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36bc12a9164f50751a0b4a623ad43bb460ed70bb 6216 F20101222_AAAYTH mahmoud_a_Page_184thm.jpg 4251245b3b588cddd24b13c4a2cdc8d6 adbdcc6b454978e0b32f622db203041ac351e35a F20101222_AAAXJD mahmoud_a_Page_041.tif 6d67a406b4508719eaa62bf58178f902 bac94b0fc708c6e8162294a32925e86deadc522a 1051914 F20101222_AAAWZV mahmoud_a_Page_065.jp2 3abec6021bf473581a017d9ff4d50d65 421ecbcc0a6329ed001ce8efa40932b7b005e18f ANALYTICAL AND EXPERIMENTAL INVESTIGATION OF ROTARYVANE TWO PHASE EXPANDERS INT VAPOR COMPRESSION REFRIGERATION SYSTEMS By AHMAD MOHAMED MAHMOUD A DISSERTATION PRESENTED TO THE GRADUATE SCHOOL OF THE UNIVERSITY OF FLORIDA IN PARTIAL FULFILLMENT OF THE REQUIREMENTS FOR THE DEGREE OF DOCTOR OF PHILOSOPHY UNIVERSITY OF FLORIDA 2008 O 2008 Ahmad Mohamed Mahmoud I dedicate this work to God Almighty in partial fulfillment of His mandate to seek Knowledge: To my loving wife Iman, daughter Salma, family and friends, without whose enduring patience and support this work would not have been possible. ACKNOWLEDGMENTS I would like to begin by thanking God for giving me this great opportunity to learn and for putting in my path wonderful people who have helped me and shown me the way. I want to thank all those people, and will try my best to remember them all here. I want to start by thanking my wife, Dr. Iman M. AlNaggar. To put it simply, this would not have been possible without her love, support and daily dose of nagging! I would like to thank my parents, Dr. Mohamed Abdelmoneim Mahmoud and Mrs. Faten Ismail Mahmoud for preparing me for and supporting me during graduate school. I also thank them for their unconditional love and endless prayers that have kept me on track. I would like to thank my mentors Dr. S. A. Sherif and Dr. William E. Lear for their time, support, guidance and patience. Their technical and nontechnical mentorship drove me to excel at whatever I did, by following their example, and helped me become the researcher I am today. I am truly grateful. I would like to thank my committee members for their guidance and input: Dr. Gary Ihas, Dr. D. Yogi Goswami, and Dr. Skip Ingley. I have been fortunate to have a diverse, knowledgeable committee that had answers to my questions, solutions to my problems, and great advice and encouragement. I would like to thank all the people in the Sherif and Lear Labs, especially Mr. Ayyoub Mehdizadeh, that have helped me throughout my years in graduate school, as well as make my long hours in the lab enj oyable. I would especially like to thank Mr. John Crittenden, engineering director at Triad Research Corporation Inc., for the guidance and knowledge he passed on to me regarding experimentation and solving countless technical challenges. I am honored to have worked with him. I would also like to thank all the staff that has assisted me greatly at UF (Department of Aerospace and Mechanical Engineering). I would like to thank my friends who have made my years in Gainesville more enjoyable: Mr. Ibrahim Taman, Mr. Ahmed ElMahdawy, Mr. Ahmed ElHady ElMahdawy, Mr. Farouk Dey, Mr. Safwat Mohammad, Mr. Mahmoud Enani, Mr. Ramadan Ajredini, Dr. Mujahid Abdul rahim and Dr. Fares AlBitar, to name a few. I would like to acknowledge the support from the Air Force Research Labs for partially funding my research and graduate education: Dr. Aly Shaaban, Dr. Ragab Moheisen and Mr. Reza Salavani. Finally, I would like to thank the University of Florida and the College of Engineering for providing such a rich and competitive graduate program in which I am very lucky to have been a part. TABLE OF CONTENTS IM Le ACKNOWLEDGMENT S .............. ...............4..... LI ST OF T ABLE S ................. ...............9................ LIST OF FIGURES .............. ...............10.... NOMENCLATURE .............. ...............17.... AB S TRAC T ......_ ................. ............_........2 CHAPTER 1 INTRODUCTION AND OBJECTIVES ................. ...............24................ Introducti on ................. ...............24................. Obj ectives ................. ...............24.......... ..... 2 LITERATURE REVIEW ................. ...............28................ Expanders in Refrigeration and Heat Pump Systems ................ ..............................28 Conventional Heat Pump and Refrigeration Systems .............. ...............29.... Transcritical Carbon Dioxide Systems ................. ...............37................ Gas Refrigeration Cycles and Cryogenics............... ...............4 Expander Selection ................ ...............45................. 3 PARAMETRIC ANALYSIS OF CYCLES .............. ...............46.... Ideal Cycles .............. ...............46.... Base Cycle ................. ...............47................. Economizer Cycle ................... ........ ..............4 Internal Heat Exchanger (IHX) Cycle ................. ...............50........... ... Actual Cycles............... ... ....... .. ...........5 Effect of Subcooling on System Performance............... ..............5 Effect of Superheating on System Performance ................. ........... ... ............. .....53 Evaluation of CFC, HFC and Transcritical CO2 Refrigeration Cycles ................ ...............54 Performance and Size Optimization of Compression Refrigeration Systems ................... .....70 Pure Hydrocarbons as Refrigerants .............. ...............83.... 4 MATHEMATICAL MODEL OF AN IDEAL ROTARYVANE EXPANDER. ........._......124 Literature Review of Modeling of Rotaryvane Expanders .........._.._.. ......._.._...........124 Model Development ........._.._.. ...._... ...............125.... Thermophy sical Model ................. ...............126........ ...... Geometric and Kinematic Model............... ...............126. Thermodynamic Model .............. ...............128.... Charging Process ............. ...............129..._ _........ Expansion Process ....._ .................. ...............131...... Exhaust process .............. ...............132..._ _........ Ideal Expander Evaluation .............. ...............133.... 5 PRIMARY AND SECONDARY LOSS MECHANISMS INT ROTARYVANE TWO PHASE REFRIGERATING EXPANDERS .............. ...............154.... Primary Loss Mechanisms ................. ...............154............... Internal Leakage Paths and Clearances .............. ...............155.... Types of TwoPhase Leakage Losses ................... .......... ...............156..... Axial Clearance Between Rotor and End Plates .............. ...............161.... Leakage around tips of vanes ................. ...............166.......... ... Leakage past the sides of the vanes ................... ........ ...... .. ..... ........ ............16 Leakage between the faces of the vanes and the side walls of the rotor' s slots ............168 Leakage in radial gap between the rotor and stator cylinder............. ............__ ...168 Friction M odel .............. ......... ........ .. .... ...........16 TwoPhase Throttling Losses in the Inlet and Exhaust Ports ................ ............ .........180 Conventional Inlet to Expander Cavity .............. ...............184.... Modified Inlet to Expander Cavity ............... ... ...............187.......... .... Thermodynamic Model of the Actual Expansion Process ................. ........................188 Charging Process ................. ...............188................ Expansion Process ................. ...............189................ Exhaust process .................. ...............190......... ...... Expander Performance Evaluation ............... ....... ..............19 Performance Variation Due to StatorCylinder Geometry .............. .....................9 Heat Transfer ................. ...............198......... ...... 6 EXPERIMENTAL PROGRAM ................. ...............214................ Experimental Facility............... .... ............21 Chilled Water/Heated Water Loop ................. ...............214............... Data Acquisition System .............. .. ...............215... Unmodified Chiller Experimental Procedures............... .............. ...........1 Dynamometer Selection, Data Acquisition and RealTime Control Scheme.......................218 Rotaryvane Ex pander Selection .............. .... ...............220. Modified Automotive Airconditioning Compressor ....._____ .........__ ..............220 Performance of Modified Compressor .......................__ ......__ ...........2 Design Issues ............... ....._ ...............223.... Designed and Machined Expander ....__ ......_____ .......__ .............2 Performance of Machined Expander ....__ ......_____ .......___ ...........25 Modified AirMotor............... ...............22 SinglePhase Experiments .............. ...............229.... Sum mary ............ ..... .._ ...............2 1... 7 CONCLUSIONS AND RECOMMENDATIONS .............. ...............250.... Internal Leakage Losses .............. ...............250.... Friction ................. ...............251................ Other Issues ............... .... .. ..... .. ........ 5 Leakage ratio, Expander sizing and Integration Concepts .............. .....................5 Recommendations............... ............25 Summary of Contributions .............. ...............256.... LIST OF REFERENCES ................. ...............258................ BIOGRAPHICAL SKETCH .............. ...............267.... LIST OF TABLES Table page 31 Summary of the percent changes in the system COP, refrigerating capacity and required work input by the addition of an expansion device for the ideal and actual R13 4a singlestage, economizer and IHX cycles ................ ...............92........... . 32 Percentage of cycle irreversibility due to the various components in basic and modified R22, R134a and transcritical CO2 Systems ................ .........................113 33 Hydrocarbons viewed as potential refrigerants ................. ................. ......... ..11 41 Summary of rotaryvane literature ................. ...._.._ ...............143 .... 42 Geometrical input parameters ................. ...............145............... 43 Typical operating conditions for a basic and modified 2 ton system .............. ................148 51 Primary leakage paths in a rotaryvane expander ................. ............... ......... ...200 52 Governing equations and their discretized form describing onedimensional adiabatic Fannoflow from a reservoir ................. ...............201............... 53 Variation of operational and dimensionless parameters to model flow in axial gap as laminar and with a zerothorder approximation............... .............20 54 Comparisons of contraction coefficients for turbulent singlephase flow.............._.... ....209 55 Variation of volumetric efficiency and final pressure as a function on inlet angle in an expander with throttling losses accounted for. ................. ....._._ ............... ..211 61 Experimental Thermodynamic State Points............... ...............241 62 Parameters used to calculate saturation properties. ............. ...............244.... 63 Machining modifications made to GAST NL32NCC1 to optimize geometric volum e ratio .............. ...............247.... LIST OF FIGURES FiMr page 31 A schematic of the ideal base cycle and the modified base cycle with an expansion device ................. ...............86....... ...... 32 Ts and Ph diagrams of the ideal base cycle and the modified base cycle with an expansion device............... ...............87. 33 Ts and Ph diagrams of the economizer cycle and an economizer cycle with an expansion device as a throttle valve replacement ................. ...............88........... .. 34 A schematic of the economizer cycle and an economizer cycle with an expansion device as a throttle valve replacement ................. ...............89............... 35 A schematic of the IHX cycle and the modified IHX cycle with an expansion device as a throttle valve replacement .............. ...............90.... 36 Ts and Ph diagrams of the IHX cycle and the modified IHX cycle with an expansion device as a throttle valve replacement ................. ...............91........... .. 37 Variation of ACOP, between the modified cycle with an expansion device and the ideal cycle (R134a), with evaporating temperature for A) To 25oC, B) To45oC for the base, economizer and IHX cycles ................ ...............93............... 38 Variation of AQe and AWnet, between the ideal modified cycle with an expansion device and an ideal base cycle, with evaporating temperature for various condenser temperatures in a singlestage vaporcompression refrigeration unit. ............... ...............94 39 Variation of ACOP, between the modified cycle with an expansion device and the ideal cycle, as a function of the evaporating temperature for both R22 and R134a for various expander efficiencies To45oC .............. ...............95.... 310 Variation of ACOP, between the modified cycle with an expansion device and the ideal cycle, as a function of the evaporating temperature for various condenser temperatures for the actual and ideal cycle configurations of the economizer cycle. .......96 311 Variation of ACOP, between the modified cycle w/ an expansion device and the ideal cycle, as a function of the evaporating temperature for various condenser temperatures for the actual and ideal cycle configurations of the IHX cycle ................... .97 312 Variation of refrigerating efficiency as a function of the evaporating temperature for both the base (no expander) and ideal and actual modified cycle with and an expander at a condenser temperature of To45oC ........._.._ .......___ ......._.._ ......98 313 Variation of refrigerating efficiency as a function of the evaporating temperature for the actual base, IHX and economizer cycles with an expander at a condenser temperature of Te=25oC .............. ...............98.... 314 Variation of an ideal system's COP as a function of the degree of subcooling for various condensing temperatures ................. ...............99......__ .... 315 Variation of an ideal system's COP as a function of the degree of subcooling for various condenser temperatures and expansion processes............... ...............10 316 Variation of the refrigerating effect as a function of the degree of subcooling for various condenser temperatures and expansion processes............... ...............10 317 Variation in an ideal system's COP with respect to the evaporator temperature for different degrees of sub cooling and expansion processes .............. ....................10 318 Variation of the difference in system COP,%, between the ideal cycle and modified cycle with an expansion device as a function of the evaporator temperature for various condenser temperatures and degrees of sub cooling ................. .....................103 319 Variation of the difference of the system COP, %, base cycle and modified cycle with an expansion device as a function of the degree of superheat in the evaporator for various condenser temperatures. ............. ...............104.... 320 Variation of the refrigerating effect for an ideal cycle as a function of the degree of superheat for various condenser temperatures ................. ...............105........... ... 321 Ts diagram of the basic system and the modified system with an expansion device for a A) conventional refrigeration system and B) transcritical CO2 refrigeration system .............. ...............106.... 3 22 Variation of system coefficient of performance as a function of heat rej section pressure for various evaporating temperatures for basic and modified transcritical CO2 System s ................. ...............107........ ...... 323 Percentage of cycle irreversibility associated with the heat rej section and expansion processes as a function of heat rej section pressure for basic and modified transcritical CO2 Systems ................. ...............107................ 3 24 Coefficient of performance of basic and modified R22, R134a and transcritical CO2 systems as functions of the evaporating temperature ................ ......... .................108 325 Difference in coefficient of performance between basic and modified R22, R134a and transcritical CO2 Systems as functions of the evaporating temperature ................... .108 326 Difference in refrigerating effect between basic and modified R22, R134a and transcritical CO2 Systems as functions of the evaporating temperature ................... ........109 327 Difference in system input work between basic and modified R22, R134a and transcritical CO2 Systems as functions of the evaporating temperature ................... ........109 328 Volume ratio of the expander employed in modified R22, R134a and transcritical CO2 Systems as functions of the evaporating temperature. .....__. ............ ....... ........1 10 329 Difference in coefficient of performance between basic and modified R22, R134a and transcritical CO2 Systems as functions of expander isentropic efficiency ................1 10 330 Percentage of cycle irreversibility due to various components in a modified R22 system as functions of the evaporating temperature ................. .......... ................11 1 331 Percentage of cycle irreversibility due to condensing process in basic and modified R22 and R134a systems as functions of the evaporating temperature ................... .......11 1 332 Percentage of cycle irreversibility due to the expansion process in basic and modified R22, R134a and transcritical CO2 Systems as functions of the evaporating tem perature ................. ...............112......... ...... 333 Dimensionless system irreversibility in basic and modified R22, R134a and transcritical CO2 Systems as functions of the evaporating temperature ................... ........1 12 334 Variation of dimensionless COP, expander work output, expander volume ratio and condenser capacitance as a function of dimensionless refrigerating effect ........._._........113 335 Variation of dimensionless expander work output and expander volume ratio as a function of evaporating temperature for various degrees of subcooling in the condenser ........._.__...... ._ __ ...............114.... 336 Variation of dimensionless condenser capacitance as a function of evaporating temperature for various degrees of subcooling in the condenser. ........._._... ................1 14 337 Variation of dimensionless condenser capacitance as a function of degree of subcooling in the condenser for various values of condenser effectiveness. ................... 115 338 Variation of dimensionless expander work output as a function of degree of sub cooling in the condenser for various expander efficiencies ........._._... ........._......115 339 Variation of dimensionless expander volume ratio as a function of degree of sub cooling in the condenser for various expander efficiencies ........._._... ........._......116 340 Variation of dimensionless COP as a function of degree of subcooling in the condenser for various expander efficiencies ....._.__._ .... ... .___ .....__... .........16 341 Variation of dimensionless COP as a function of degree of subcooling in the condenser for various evaporator degree of superhea. ....._.__._ ........___ ...............117 3 42 Variation of the refrigerating effect as a function of evaporating temperature for various refrigerants at a condensing temperature of A) 25oC and B) 45oC for the ideal base cycle ................. ...............118............... 343 Variation of the ideal base cycle coefficient of performance as a function of evaporating temperature for various refrigerants at a condensing temperature of A) 25oC and B) 45oC ................. ...............119............... 3 44 Variation of compressor work as a function of the evaporating temperature at a condensing temperature of A) 25oC and B) 45oC for various refrigerants in an ideal base cycle ................. ...............120................ 345 Variation of the increase of COP (when comparing the base cycle and the expander cycle) as a function of the evaporating temperature for various refrigerants at a condensing temperature of A) 25oC and B) 45oC ................ ................. ......... .12 346 Variation of the decrease in network (when comparing the base cycle and the expander cycle) as a function of the evaporating temperature for various refrigerants at a condensing temperature of a) 25oC and b) 45oC ................. ......... ................1 22 347 Variation of the increase in refrigerating effect (when comparing the base cycle and the expander cycle) as a function of the evaporating temperature for various refrigerants at a condensing temperature of a) 25oC and b) 45oC............... .................. 123 41 Flow diagram of the main computer program developed ................. .......................142 42 Schematic of a generally oriented circular rotaryvane expander with 8 vanes described by two circular arcs ................. ...............144........... ... 43 Variation of the inlet throat area with respect to angular displacement ................... .......146 44 Variation of the exit throat area as a function of angular displacement for an 8vane circular M VE .............. ...............146.... 45 Pressure variation as a function of volume in an ideal expander for the cases of ideal, over and under expansion. ............. ...............147.... 46 Variation of builtin volume ratio as a function of intake angle for different numbers of vanes ................. ...............149......... ...... 47 Variation of ideal volume as a function of angular displacement for different numbers of vanes ................. ...............149............... 48 Variation of ideal and actual volumes as a function of angular displacement. ................150 49 Variation of pressure as a function of volume for various intake angles. ................... .....150 410 Variation of pressure as a function of volume for different numbers of vanes ...............15 1 411 Variation of mass within the expander' s cell volume as a function of angular displacement for various intake angles ................. ...............151........... ... 412 Variation of power as a function of angular displacement for different numbers of vanes .............. ...............152.... 413 Variation of power as a function of angular displacement for various intake angles......152 414 Variation of power as a function of volume ................. ...............153........... . 51 Schematic of nomenclature used and leakage paths of a circular rotaryvane expander with general orientation and a (a) conventional or (b) modified intake ports..199 52 Schematic of a typical leakage path ................. ...............200........... .. 53 Shear and pressure driven Couette flow .............. ...............201.... 54 Nonaxisymmetric pressure boundary condition on outer surface of the rotor ...............202 55 Freebody diagram of a vane protruding outward from a rotor slot at a local angle 6 ....203 56 Schematic of generalized Couette flow in the axial gap between rotor and endplate....204 57 Variation of reaction forces on a vane with no vanetip curvature as a function of angular displacement .............. ...............204.... 58 Variation of reaction forces on a vane with a circular vanetip profile as a function of angular displacement .............. ...............205.... 59 Variation of leakage from/to the expander cavity as a function of angular displacement due to nonaxisymmetric flow between the rotor and stationary end plates for different intake angle spreads .............. ...............205.... 510 Variation of nonaxisymmetric leakage from/to the expander cavity for the ideal and throttling cases .............. ...............206.... 511 Variation of leakage from/to the expander cavity through the gap between the sides of the vanes and endplates for different intake angle spreads ................. ................. .206 512 Variation of leakage to the expander cavity from the rotor slot (modified intake) through the gap between the face of the vanes and rotor slot ................. .........._ ....207 513 Variation of the ideal and actual mass flowrates through the expander as a function of rotational speed ........... _... ......... ...............207.... 514 Variation of the ideal and actual mass flowrates through the expander as a function of the number of vanes ................. ...............208......_..... 515 Comparison of way by which fluid is introduced into the expander' s cavity; A) conventional intake via intake port and B) modified intake via rotor slots through endplates to ensure vanetip and statorcylinder contact............... ...............208 516 Flow through a sudden contraction............... ..............20 517 Schematic of the three phases of vane orientation that occur during the intake process.210 518 Variation of pressure in expander cavity as a function of angular displacement for the ideal and actual (throttling only) cases ................. ...............211.............. 519 Schematic of the intake port of the modified rotaryvane intake through the end plates and into the rotor cavity via rotor slots ................. ...............212........... . 520 Schematic of (a) symmetric (b) nonsymmetric noncircular rotaryvane expander comprised of four circular arcs (14) and a sealing arc (5) ................. ......................212 521 Variation of vane displacement as function of the leading vanes' angular displacement for both a circular and noncircular MVE .............. ....................21 522 Variation of vane velocity as function of the leading vanes' angular displacement for both a circular and noncircular rotaryvane expander ......____ ........._ ........._....213 61 The water heater used to add a constant heat load to the constant temperature water loop .............. ...............236.... 62 Unmodified two ton aircooled barrel type water chiller ................. .......................236 63 Instrumentation map and schematic of the experimental setup for a vapor compression cycle with a bypass loop for rotaryvane expander integration.................237 64 Variation of the measured pressure for the standard mode of operation in the unmodified chiller as a function of time ......___ .........___....._ ...........3 65 Variation of the measured temperature for the standard mode of operation in the unmodified chiller as a function of time ....__ ......_____ .......___ ...........3 66 Variation of the measured pressure for the cutoff mode of operation in the unmodified chiller as a function of time ....__ ......_____ .......___ ...........3 67 Variation of the measured temperature for the cutoff mode of operation in the unmodified chiller as a function of time ....__ ......_____ .......___ ...........3 68 Variation of the compressor work for both the cutoff and standard modes of operation in the unmodified chiller as a function of time ....._____ ...... ....__...........240 69 Schematic of the cutaway view of the bypass loop and evaporator and the logic behind the continuous control scheme used to control the degree of superheat .............243 610 Flow path of refrigerant in both the compression and expansion processes.. ................. .245 611 Double acting, five vane modified automotive compressor .............. .....................4 612 Unmodified, modified symmetric and nonsymmetric noncircular Expander (All dimensions in inches)............... ...............248 613 Schematic of the experimental setup for compressed air and R22 tests with a rotaryvane expander .............. ...............249.... 71 Variation of the criticalpressure ratio as a function of condensing temperature for a twophase expander and vapor compressor ................. .........._ ....... 257......... 72 Expander sizing diagram............... ...............257 NOMENCLATURE 0 reference state, zerothorder 1 inlet state, location of minimum volume (i.e. cutoff) 2 location of maximum volume (i.e. at exhaust) A crosssectional area, m2 a speed of sound, m/s Acc(6) sliding acceleration of vane, m/s2 act actual Ak, Bk Fourier constants amb ambient b base cycle, boundary work, backpressure c Carnot calc calculated Cd discharge coefficient comp compressor cond condenser COP coefficient of performance, dimensionless CP critical point C, specific heat at constant pressure, kJ/(kg K) crit critical cy control volume (i.e. expander cavity) dt differential in time, s e eccentricity m, evaporator, electric, exit state E total energy, kJ econ economizer cycle ED expansion device Eu Euler number ex start of exhaust port exh exhaust exp expansion device f Darcy friction coefficient F force, N f saturated liquid, friction g saturated vapor, acceleration of gravity m/s2 gc gas cooler h specific enthalpy kJ/kg, evaporator coolant, isenthalpic Hv height of vane, m i inlet, intermediate I specific irreversibility (kJ/kg), current (Amp) in inlet state, spread of intake port int intake L axial length of expander, m 1 leakage channel length, m leak corresponding to internal leakage Lv axial length of vane, m M Mach number m mass kg, mean mi mass flowrate, kg/s max maximum MW molecular weight, kg/kmol Nv number of vanes O center, location o original out outlet state P pressure, kPa p dimensionless pressure, pr= (p p x)l(p, P ) q specific heat transfer, kJ/kg Q heat transfer rate, kW F dimensionless radial coordinate, F = r /rR r reservoir R rotor ref refrigerant, refrigerating Reel Reynolds number based on axial gap width RR rotor radius, mm RS(6) distance from statorcylinder' s center to periphery, m r, volume ratio (process or builtin) S gap aspect ratio, statorcylinder s specific entropy kJ/kgK, isentropic sc subcooling sf sliding friction sh superheat sys system T temperature K, torque Nm t time, s or minutes (unless otherwise noted) tv thickness of vane, m (=ts, slot thickness) u specific internal energy kJ/kg, velocity m/s u dimensionless radial velocity, u = u airR v dimensionless azimuthal velocity, v = vlirR v throttling valve, vane, specific volume m3/kg V voltage V, volume m3 vd viscous drag Vel(6) sliding velocity of vane, m/s w dimensionlesss axial velocity, w= w/04~ w specific work, kJ/kg W power, kW x quality, dimensionless X(6) vane height protruding from slot, m z dimensionless axial coordinate, z = z /6 A differential 0Z speed of angular rotation, RPM oc void fraction P inner to outer radius ratio 8 angle between successive vanes, degrees, leakage channel height, m Si axial gap between rotor and endplate, m 82 radial gap between rotor and stator during sealing arc, m E effectiveness, dimensionless r efficiency h leakage path flow coefficient C1 dynamic viscosity, CIPa s 6 angular displacement/local angle, degrees 8cut angle at which expansion process begins, degrees 6ex spread of the expander' s exhaust port, degrees 6in spread of the expander' s intake port, degrees p density, kg/m3 co angular velocity, rad/s 9 stream availability or exergy, angle between base line and line through stator center from rotor' s center, degrees Abstract of Dissertation Presented to the Graduate School of the University of Florida in Partial Fulfillment of the Requirements for the Degree of Doctor of Philosophy ANALYTICAL AND EXPERIMENTAL INVESTIGATION OF ROTARYVANE TWO PHASE EXPANDERS INT VAPOR COMPRESSION REFRIGERATION SYSTEMS By Ahmad Mohamed Mahmoud August 2008 Chair: S. A. Sherif Cochair: William E. Lear Major: Mechanical Engineering The refrigeration and airconditioning community has been searching for environmentally friendly refrigerants and ways to improve energy efficiency and to increase the potential for reductions in system size and weight for some time. These system improvements may manifest themselves in numerous ways but significantly impact terrestrial logistics differently. This study investigates the analytical and experimental utilization of rotaryvane expanders as throttle valve replacements in vapor compression refrigeration systems with a specific application of these expanders in smaller deployable environmental control units. The findings support the conclusion that utilizing twophase expanders in refrigeration systems is very promising. Mathematical models for a systemlevel parametric cycle analysis were developed to assess potential gains in the cycle coefficient of performance for R22, R134 and transcritical CO2 vapor compression technology. Optimization studies were conducted to determine the optimum performance of a refrigeration system subj ect to constraints of size and weight of both the condenser heat transfer area and the size and weight of the twophase expander. An exhaustive literature survey aids and validates the suitability of the type of positive displacement expander used, after which comprehensive component level thermodynamic and fluid dynamic models of a rotaryvane expander were developed to establish the performance of this expansion device as a function of design and fluid parameters. This included rigorous modeling of irreversible loss mechanisms such as throttling in the intake and exhaust ports, two phase internal leakage, friction, recompression, and under or overexpansion due to incorrect sizing of the expander or offdesign operation. Results from these models were used to establish the operating principles of a twophase rotaryvane expander. Experimental data gathered after modifying a conventional chiller with an alternative flow path, where a rotaryvane expander and dynamometer have been installed, were used to improve the fidelity of the analytical model developed. Issues such as realtime control to satisfy systemlevel constraints, expander sizing and operational speed and inadequate operation were addressed. The analytical model developed along with singlephase experimentation were used to understand and overcome componentlevel complications and inadequacies due to irreversible effects. CHAPTER 1 INTRODUCTION AND OBJECTIVES Introduction The refrigeration and airconditioning community has been searching for environmentally friendly refrigerants and ways to improve energy efficiency and to increase the potential for reductions in system size and weight for some time. Cycle improvements may manifest themselves in many ways such as using multistage compression with intercooling and/or flash gas removal as a means to reduce the work input to the compressor, employing economizers and/or employing expansion devices to recover work. There are two advantages to using expansion devices with output work. The first is that lower enthalpy refrigerant is obtained at the inlet of the evaporator and hence increases the refrigerating effect of the evaporator. The second is the extra work that can be extracted from the expansion process, which can then be used to lower the input requirement of the compressor or to operate auxiliary machinery such as fans or pumps. Both effects serve to increase the coefficient of performance (COP) and hence raise the energy efficiency of the system as well as increase the potential for reductions in system size and weight. Objectives The proposed overall approach is to combine experimentation with thermodynamic and fluid dynamic modeling in order to demonstrate the operating principles, to discover any unanticipated difficulties, and to establish a qualified design code which may subsequently be used for optimizing airconditioning and refrigeration systems for a wide range of applications. A detailed list of these obj ectives is as follows: *Conduct a literature survey of work on the use of various expansion devices in relevant engineering cycles. This exhaustive survey would aid and validate the suitability of the selected type of positivedi splacement expander used. * Perform systemlevel parametric analysis of vaporcompression refrigeration systems to assess potential gains in the cycle COP. This includes examining the factors that affect reduced power requirements and increased refrigerating capacity. * Develop a thermodynamic and fluid mechanic componentlevel model of twophase rotaryvane expanders to establish their efficiency as a function of design and fluid parameters. * Develop a comprehensive model of primary irreversible effects such as internal leakage, friction, and throttling within the twophase expander and present relevant discussion or models of secondary losses. * Design, build and modify an experimental refrigeration system to incorporate a rotaryvane expander based on model inputs including rotaryvane expander sizing and rotational speed. * Develop an appropriate realtime control scheme to mimic the operational function of conventional thermostatic expansion valves, i.e. to regulate mass flowrate through the rotaryvane expander, to satisfy systemlevel constraints. * Utilize the developed computer program and comprehensive singlephase experimentation to understand, recommend and possibly overcome componentlevel complications and inadequacies due to irreversible effects. * Utilize the experimental results where necessary to improve the fidelity of the qualified design code. Based on the motivation behind and obj ectives of this investigation, a detailed review of recent literature pertaining to the use of expanders as throttle valve replacements in refrigeration units was conducted. The review entails the use of twophase expanders in conventional vapor compression refrigeration systems with conventional CFC, HCFC and HFC refrigerants as the working fluids. The review also encompasses the use of twophase expanders in geothermal systems and transcritical carbondioxide refrigeration cycles as well as singlephase expanders utilized in organic Rankine power cycles and gas refrigeration cycles. This section will enable the reader to understand the fundamentals of this technology as well as highlight practical issues/problems that may have been presented by various researchers in this regard. The type of expander used was chosen and suitability was based on this exhaustive review. Analytic parametric modeling of the ideal and actual vapor compression refrigeration cycle and modified cycles such as the vapor compression cycle with an expander, a liquidtosuction heat exchanger and a multistage vapor compression cycle with an economizer was then conducted. These cycles have been analyzed in both ideal and actual cases and have also been analyzed with the additional modification of utilizing a twophase expander as a throttle valve replacement. The working fluids investigated in this study include: R12, R22, R134a, pure hydrocarbons and transcritical carbondioxide. Optimization studies were also conducted to determine the optimum performance of a refrigerating unit subj ect to constraints of size and weight of both the heat transfer area and the size and weight of the twophase expander. The development of a detailed thermodynamic and fluid dynamic model of the rotaryvane expander followed. The geometry, kinematics and thermodynamics of a circular rotaryvane expander were described mathematically to determine its ideal performance as a function of design and fluid parameters. A robust thermodynamic model that takes into account primary loss mechanisms such as friction and internal leakage and presents a discussion, models when necessary, of secondary irreversible effects such as throttling in the intake and exhaust ports, twophase internal leakage, friction, recompression and under or overexpansion due to incorrect sizing of the expander is then described. An experimental program that has been developed at the University of Florida for testing the use of a twophase rotaryvane expander in a refrigeration unit is then detailed. The equipment and instrumentation used in the lab to gather experimental data to validate and improve the fidelity of the analytical models are described. The sizing and selection of the rotaryvane expander and the dynamometer is presented. Finally the means of realtime control of the expander via a highspeed programmable dynamometer controller is presented. The developed computer program and comprehensive singlephase experimentation was used to understand, recommend and possibly overcome componentlevel complications and inadequacies due to irreversible effects such as friction and internal leakage. A summary of key technical challenges, recommendations and conclusions from both the comprehensive modeling and experimental effort is then presented. CHAPTER 2 LITERATURE REVIEW The concept of utilizing expansion devices in various thermodynamic cycles is one that has been described in scattered technical literature. Example applications in which expanders have been used to recover and utilize lost work or waste heat include geothermal applications, Organic Rankine Cycles (ORC), and refrigeration cycles. A thorough understanding of these applications along with the types of working fluids used, the types of expansion devices used and inherent loss mechanisms within those expansion devices will allow further advancement of such concepts. In literature dealing with expansion devices, the working fluid has been predominantly air, steam, refrigerant vapor or transcritical carbondioxide. In the present study, expansion takes place in a refrigerant' s twophase region where additional complexities (e.g. erosion due to cavitation and increased internal leakage due to significant density variation) arise. Although complexities exist with the expansion of gases, vapors, and transcritical fluids, the loss mechanisms of internal leakage, friction, and heat transfer and how they affect overall performance of different types of expanders are qualitatively comparable to one another. Understanding and incorporating these effects will aid in developing a mathematical model of a twophase expander employed in a vapor compression refrigeration/heat pump system. Expanders in Refrigeration and Heat Pump Systems There has been much effort to quantify the amount of savings and the methods by which the work recovered and additional refrigerating effect could be utilized from the use of expanders in refrigeration and heat pump systems. Among the researchers who investigated this are Zhang and Yu (1992), Markoski (2003) and Brasz (1995). Zhang and Yu (1992) compared ideal and modified refrigeration cycles for R12, R22, R 502 and R707. They found savings from utilizing twophase expanders and recommended the use of expanders. They failed to elaborate on the complexities associated with utilizing expanders in the twophase region. They mention only that components of the expander are small and hence friction losses are large and that problems may arise from lubrication related issues. Brasz (1995) introduced the use of a turboexpander in large (>85 tons) vaporcompression refrigeration systems utilizing R134a as the working fluid. According to Brasz, a turbine efficiency of 39% could overcome the disadvantages of using R134a instead of lowpressure R 11 or R123 refrigerants. He concluded that the application of this technology is applicable where the expander rotational speed matches that of an existing drive train. Markoski (2003) presented three alternative methods by which the expansion work from an expansion engine can be utilized in a vapor compression refrigeration cycle. The author provides brief guidelines and analyses for the use of the power recovered by the expander in conventional and nonconventional vapor compression cycles as well as powering a circulation pump for liquid circulation through a flooded evaporator. Conventional Heat Pump and Refrigeration Systems The use of expansion devices in conventional vaporcompression refrigeration cycles has been investigated by Hays and Brasz (1996, 1998), Smith and Stosic (1995), Zoughaib and Clodic (2003), Smith et al. (1994, 1996, 1999, 2001a, 2001b), Brasz et al. (2000), Kornhauser (1990), Fischer (1978), Kim et al. (2004), Tamura et al. (1997), Disawas and Wongwises (2004), Henderson et al. (2000) and Taniguchi et al. (1983). In most of the aforementioned studies, unless mentioned otherwise, a throttling valve was used as the default control mechanism responsible for ensuring the degree of superheat of the refrigerant leaving the evaporator. The use of a throttling valve would however cause a loss in the available pressure difference that may be utilized in an expansion device for work recovery. Tamura et al. (1997) investigated the use of a screw expander in a high temperature (up to 180oC) binary heat pump with steamwater and ammonia as the working fluids. They found a COP improvement of about 40% when comparing a hightemperature heat pump with one employing an isentropic screw expander and one without in the operating range of 40180oC. Fisher (1978) described the concept of a pivotingtip rotaryvane compressor and expander applied to a solarpowered vaporcompression heat pump. The solar heat pump had a capacity of 3 tons and R12 was selected since the author found that the required compressor and expander displacements are of reasonable size to provide good efficiencies and low manufacturing costs. Compression and expansion characteristics were taken into consideration before selecting the working fluid as to avoid entirely the complexities that arise when expanding into the twophase regime. The author also describes the performance of pivotingtip gas bearings, which were utilized to reduce vanetip friction in rotaryvane turbomachinery. Estimated efficiencies of 85% were assumed for both the compressor and expander to reflect improvements that the pivoting tip gas bearings will introduce. A cooling coefficient of performance of 0.56 at design conditions was achieved. Taniguchi et al. (1983) presented a detailed analytical and experimental investigation of helical screw twophase expanders in large refrigeration systems whose working fluid is R12. They stated the added advantage of utilizing positive displacement turbomachinery as twophase expanders because they operate without erosion and slip losses between liquid and vapor phases. The authors investigated the degree of subcooling on the performance characteristics of this modified vapor compression cycle. Effects of vapor formation during the expansion process as well as internal leakage losses were accounted for in the theoretical model. The helical screw expander used in this study had a builtin volume ratio of 5:1. The expansion process volume ratio of R12, at the operating conditions, however depended on the degree of subcooling in the condenser and varied from 13.2:1 and 10.6:1 corresponding to 0 and 12 K of subcooling respectively. The authors concluded that the isentropic efficiency of the expander increased from 30 to 60% at rotational speeds of 500 and 3000 rpm respectively. The authors predicted analytically an isentropic efficiency approaching 80% for larger screw expanders. Kornhauser (1990) analytically investigated the use of a twophase ej ector as a refrigerant expander to replace the throttling process in a vaporcompression refrigeration system. The author cites other expansion devices as expensive and susceptible to damage because of two phase flow. The power that is recovered by the expander is not extracted or coupled in any way but is used to partially compress the refrigerant leaving the evaporator. The effects of both isentropic expansion and partial compression significantly increase the coefficient of performance of the system. The system is similar to a twostage refrigeration unit where the work extracted from the high pressure stage is used to drive the compression process of the low pressure stage. A throttling valve expands the refrigerant in the low pressure cycle to the evaporator pressure. According to the author this expansion is across a small pressure difference and is negligible when accounting for the maximum work extraction from the cycle. Theoretical calculations were made to compare the conventional and ej ector refrigeration cycles. A constant pressure mixing model of the ej ector was used. The author found that for an ideal ejector expansion cycle, an increase in the cycle coefficient of performance of 13%, 21%, 20%, 17%, and 30% would be realized for R11, R12, R22, R113 and R502 respectively. Results detailing the decrease in compressor displacement and the performance gains of R1 14, R500 and R717 are also presented. An interesting obstacle that Kornhauser (1990) eludes to is the fact the conventional expansion valve would defeat any performance improvements made by the use of an expansion device. According to Kornhauser (1990), Newton (1972a, 1972b) has patented two methods by which the liquid flow through the expander may be controlled. Controlling the mass flowrate through the ej ector may be accomplished by controlling the specific volume of the entering fluid by means of inj ecting small amounts of hot gas into the refrigerant exiting the condenser. Varying the nozzle area could also control the mass flowrate through the ejector. Disawas and Wongwises (2004) experimentally investigated the use of a twophase ej ectorexpansion device in a conventional vapor compression refrigeration system whose working fluid is R134a. They used an ejector as the sole method by which expansion occurs unlike other investigators who used a throttling device. They reported a maximum increase in COP of 2% and 10% at an evaporating temperature of 16oC and a condensing temperature of 37 and 32oC, respectively. This is not an evaporating temperature typical in airconditioning applications. The ej ector system performance, when compared to the conventional system, decreases greatly as the condensing temperature is increased and the evaporator temperature is decreased. Hays and Brasz (1996) presented a theoretical investigation of the power recovered by the use of a twophase turbine in a refrigeration system with R134a, R22, R123 and propane as the working fluids. The calculations were run assuming the turbine had isentropic efficiencies of 55 and 70%. The authors also experimentally investigated the performance of twophase turbine in a 500 ton R134a chiller. The authors determined a turbine efficiency of 6065% and discussed the turbine rotor loss mechanisms that accounted for this deficiency. Hays and Brasz (1998) report on the implementation of a standalone turboexpander as throttle valve replacement for a large 20005000 ton centrifugal chiller installation at a commercial building in Manhattan, New York. They reported that over 70 refrigeration units employing twophase turbines are in operation in a wide range of industrial and commercial applications. They concluded that at an evaporator temperature of 44oF (6.7oC) and a condensing temperature of 86oF (30oC), 15 and 180 kW of power can be produced by a 500 and 6000 ton chiller unit respectively. These values are ideal and do not take into consideration the generator efficiency. The installation cost for one of these large units is approximately $1000/kWe initially and should decrease to a minimum of $400/kWe for additional units. Zoughaib and Clodic (2003) investigated the use of a microturbine as an expansion device in a domestic refrigeration unit. The power recovery would then be used to drive an auxiliary fan(s) that would, through forced convection, ensure that no frost would form on the heat exchanger of nofrost domestic appliances. The authors parametrically investigated the effect of subcooling on the modified refrigeration cycle. The authors assumed a microturbine isentropic efficiency of 80% and hence concluded that a 1.1% increase in the coefficient of performance and 1.12 W of generated power were realized. Smith et al. (1994) investigated the thermodynamic modeling of a Lysholm machine as a twophase expander in largescale refrigeration systems utilizing R113 as the working fluid. They discussed the differences that existed between their model and the one proposed by Taniguchi et al. (1983). Among the differences that the authors pointed out was the fact that Taniguchi et al. (1983) assumed that the filling process would take place at a constant pressure. According to the authors, the filling process does not take place at a constant pressure because the acceleration of the entering refrigerant causes a pressure drop, which in turn induces flashing and thus causes higher fluid velocities. The authors estimated that isentropic efficiencies of about 7080% could be expected. Smith and Stosic (1995) describe the principle behind a novel machine, which they dubbed the "expressor" that is comprised of a coupled twinscrew compressor and twinscrew expander in a single casing. They investigated the use of this expressor unit as a throttle valve replacement in a conventional large chiller where R134a is the working fluid. The authors estimated the expander adiabatic efficiency as 70% and explained that large leakage losses do not affect the performance of the expander because they are in the direction of the bulk flow. A coefficient of performance gain of approximately 10% and 7.5% with 0 and SoC subcooling respectively was realized. A throttle valve is directly upstream of the expressor device. Brasz et al. (2000) discuss the disadvantages of this mechanism that make this technology rather expensive to implement. The primary disadvantages mentioned were the need for a timing gear, the high cost of seals and the need for two sets of rotors to carry out the compression and expansion processes. Smith et al. (1996) presented the high efficiency design of twophase screw expanders in various cycles. Smith (1993) first presented the use of these twophase expanders in a trilateral flash cycle (TFC). In this cycle a fluid is pressurized adiabatically, heated at constant pressure to its boiling point, expanded adiabatically as a twophase mixture and then condensed at constant pressure. Smith et al. (1994) then investigated the use of different working fluid mixtures to increase the power output of a twophase expander employed in the TFC. Smith et al. (1996) concluded that if "a small amount of underexpansion is permitted, high speed, low builtin volume ratio designs, with roughly half the volumetric capacity required for lower speed full expansion alternatives, attain the highest overall adiabatic efficiencies." They also reported that from a large airconditioning unit data they were able to predict a 710% increase in the coefficient of performance of the system. This could be achieved by utilizing the twophase screw expander to drive a compressor in a hermetic unit called the "expressor," (see Smith and Stosic 1995) with an adiabatic efficiency of approximately 70%. Smith et al. (1999) investigated the feasibility of utilizing a twin screw twophase expander in a large (500 ton) chiller unit that operated with R134a as the working fluid. They attained an expander adiabatic efficiency of approximately 70%. They listed the most significant factors that hinder the adoption of twophase expander in refrigeration systems as poor adiabatic efficiencies and high cost of construction and installation. They discussed the results found by Smith et al. (1996) as to the improper selection of the builtin volume of the expander when compared to the actual expansion process volume ratio. Brasz et al. (2000) presented the development of a twin screw "expressor" with only one pair of rotors as a throttle valve replacement for a large watercooled chiller. The need for a timing gear and high cost seals was avoided by the use of high profie rotors developed earlier by the authors. The compression process in the expressor unit recompresses the vapor that is generated in the expansion process by means of power that is recovered. The recompressed vapor would then be piped directly to the condenser inlet. The authors discussed the pros and cons of different methods by which the power recovered may be utilized. They indicated that the efficiency of the expandercompressor mechanism, expander and compressor is approximately 55%, 70% and 80% respectively. At part load, the speed reduction caused by the reduced flow via the throttling valve negates the use of a control system. Initially the builtin volume ratio of the screw expander was designed and built at 2.85:1. The authors found however evidence of overexpansion when this 2.85:1 expander was used with R134a and R113 whose expansion process volume ratios were 11.4:1 and 12.9:1 respectively. The authors then progressively reduced the builtin volume ratio of the expander to 1.85:1 to avoid overexpansion. Smith et al. (2001a) investigated the use of a helical twin screw compressorexpander as a replacement to the throttle valve in a refrigeration system. Poor adiabatic efficiencies as well as high manufacturing and installation costs are amongst the most significant factors hindering the extensive use of twophase expanders. According to Smith et al. (2001a) they have shown that the adiabatic efficiency of the expander, a reported maximum of 70%, is significantly higher because the builtin volume ratio of the expander is less than the volume ratio of the actual expansion process. They designed, built and tested an expander unit with a builtin expansion ratio of 2.85:1. The expander provided a 3.610.3% increase in the system coefficient of performance for an actual expansion process volume ratio of 11.4:. i Smith et al. (2001Ib) presented an economical analysis of twophase screw expanders that may be utilized in organic Rankine cycles, Trilateral Flash Cycles and refrigeration units. They reported a peak adiabatic efficiency of 76%. Although this technology could be utilized in refrigeration systems, the authors conclude that it would be more significant for Trilateral Flash Cycles (Smith, 1993 and Smith et al., 1994, 1996) Kim et al. (2004) presented preliminary results of an investigation of the use of a scroll expander with a heating structure and a proposal of their use in a refrigeration cycles as two phase expanders. When used in hightemperature and highpressure applications, clearances in both the radial and axial directions are caused by differential thermal expansion of the scroll elements. This may result in a decrease in the expander efficiency as well as the expander's specific power output. The authors investigated the use of a heat pipe that would provide a uniform temperature throughout the scroll elements by means of heating. According to the authors, if the scroll expander with a heating structure is used in twophase expansion, instances of over expansion will cause the liquid in the expander to evaporate by means of heat from the refrigerated space. They concluded that this in turn would both increase the power output of the expander and the cooling capacity of the system due to a higher volumetric expansion ratio needed in the expander. In this case the expander could also be thought of as a partial evaporator. Henderson et al. (2000) theoretically investigated the economics of employing compressor expander devices in heat pumps that use R410 as their working fluid. They investigated using a screw compressorexpander since it was found that the rotaryvane compressorexpander would likely fail because of excessive friction at the vanetip/stator surface and could also be very noisy. They found that if the device had an 80% isentropic efficiency, the system COP would increase by 30%. They have not specified the operating conditions or any component efficiencies in their study. In a maj ority of the studies, no subcooling in the condenser was allowed as to determine the maximum possible work extraction from the expansion process. This however would result in immediate formation of vapor upon the slightest decrease in pressure and increase of velocity. This in turn could cause cavitational erosion, especially in dynamic expansion devices. This phenomenon however has not been addressed directly. Transcritical Carbon Dioxide Systems The inherent coefficient of performance of a transcritical CO2 CyClC is less than the coefficient of performance of a conventional vapor compression cycle. Among the methods by which this deficiency may be overcome is to utilize expanders as throttle valve replacements. One primary difference between the use of expanders in a transcritical CO2 cycle and a conventional cycle is the fact that complexities such as cavitation only take course as the velocity of the incoming refrigerant has decreased (i.e. at later stages in the expansion process). In conventional vaporcompression cycles these complexities may occur immediately and is a strong function of the degree of subcooling and the severity of loss mechanisms during the intake phase of the expansion process. The use of expanders in transcritical carbon dioxide systems have been investigated by Robinson and Groll (1998a, 1998b), Baek et al. (2005a, 2005b), Li and Groll (2005), Huff et al. (2002, 2003), Fukuta et al. (2003), Zha et al. (2003), Nickl et al. (2002, 2003), Stosic et al. (2002), Hays and Brasz (2004), Heyl and Quack (1999), Li et. al (2000), Driver (1996), Driver and Davidson (1999), Heyl et al. (1998), Ertesvag (2002) and Preissner (2001). Robinson and Groll (1998a, 1998b) analytically investigated and compared the performance of a transcritical CO2 cycle and a conventional R22 refrigeration cycle with and without an expansion turbine. They found that use of an internal heat exchanger along with an expansion device decreased the COP of the transcritical CO2 cycle by 68%. They concluded that the stream availability following the heat rej section process in the condenser is better utilized by an expansion device rather than an internal heat exchanger. They also found a 23% COP increase when comparing an R22 refrigeration cycle and a transcritical CO2 cycle both with expansion devices with a 60% isentropic efficiency operated at an evaporating temperature of SoC and a condensing temperature of 35oC. Baek et al. (2005a, 2005b) studied both analytically and experimentally the effect of the addition of a newly designed pistoncylinder workproducing device to a transcritical CO2 cyc 0. Experimentally they found a 10% increase of the cycle COP taking into account both the increase in evaporator capacity and expansion work. The limiting factor in this study was the isentropic efficiency of the expander, which was reported to be 10% (experimentally) and 34% (theoretically). The discrepancy between the two can be attributed to the 30% uncertainty in the instruments used for measurements as well as the inadequate theoretical internal leakage model that was used. Li and Groll (2005) analytically investigated the use of an ej ectorexpansion device in a transcritical CO2 cycle. They found that the cycle COP can be increased by 16% by assuming that the ej ector has an isentropic efficiency of 90%. They have however not investigated the potential loss in efficiency due to various loss mechanisms. Heyl and Quack (1999) presented the process calculations, design and results of a novel free piston expandercompressor for a CO2 cycle. The expandercompressor device had two expansion and two compression cylinders and was assumed to have an isentropic efficiency of 85%. They noted an increase of cycle efficiency of 38.7% and 10% with and without work recovery from the expansion device. They reported an experimental coefficient of performance gain of 30%. They concluded that a significant disadvantage to this type of compressorexpander was that the expander and compressor pistons moved with identical strokes, which did not utilize all of the available expansion work (underexpansion). The operating conditions were not detailed. Nickl et al. (2002) presented a "second generation" novel piston expandercompressor that would attempt to overcome the disadvantages of the expandercompressor presented by Heyl and Quack (1999). They developed a double rocker arm that would control the different speeds of the expander and compressor pistons. They concluded that this mechanism would prove to be complex and expensive. A slight increase of the coefficient of performance relative to the "first generation" expandercompressor (Heyl and Quack, 1999) was realized. Nickl et al. (2003) presented a "third generation" novel piston expandercompressor with three expansion stages for a transcritical CO2 Cycle. According to them, this would eliminate the identical strokes of the expander and compressor pistons (Heyl and Quack, 1999) in their "first generation" expandercompressor. It would also eliminate the complex double rocker arm needed to control the different speeds of the expander and compressor pistons (Nickl et al., 2002) of the "second generation" piston expandercompressor. The author' s first estimate of the isentropic efficiency of the expandercompressor was 85% and did not take into account losses due to heat transfer, pressure drops in valves, internal leakage and friction losses. They concluded that the isentropic efficiency of the expander decreased only 3% when these losses were taken into consideration. Zha et al. (2003) developed a rotarytype rolling piston expander to use as a throttle valve replacement in a transcritical CO2 CyClC in Small heat pumps and refrigeration systems. They experimentally determined the design parameters, method of control and determined the loss mechanisms associated with this expander. They also mentioned that cavitation and liquid slugging are among the obstacles that hinder the development of CO2 expander technology. They have estimated the isentropic efficiency of the rolling piston expander to be about 50%. They have attributed the losses in efficiency to friction (~24%) and internal leakage losses (~25%). Fukuta et al. (2003) investigated and predicted the performance of a rotaryvane expander utilized in a transcritical CO2 CyClC aS a replacement to the throttle valve. They cited issues of slugging and cavitation as the main obstacles to the development of twophase expander technology. The prototype expander that was used had a builtin expansion ratio of 2:1. They initially assumed an expander efficiency of 60%. After taking into account the losses from heat transfer and internal leakage they calculated an isentropic efficiency of 43%. Huff et al. (2002) developed an algorithm that estimates the performance of the expansion and compression process in positive displacement turbomachinery. They have taken into account internal leakage losses, heat transfer and valve losses in their modeling effort. They have applied this analysis for scroll, piston, rotaryvane, rotary piston and screw type mechanisms. They have applied this analysis with particular interest to a transcritical CO2 cycle and have reported a coefficient of performance gain of 4070% and a 515% increase in capacity. The authors discussed the importance of the builtin volume ratio of the expansion device in use and the effect it may have on the high side pressure of the cycle. They concluded that if the rotational speed and builtin volume ratio of the device is not adjustable then this will ultimately reduce the benefit of the expander in a transcritical cycle. They proposed utilizing an expander and a throttling valve either in series or parallel to match the high side pressure with the optimum pressure. They concluded however that the performance gain will be relatively less than if variable rotational speed and volume ratio were employed. Huff et al. (2003) experimentally investigated the use of two R134a scroll expanders in a transcritical carbon dioxide cycle. The first prototype was modified by reducing the wall height of the original compressor scrolls. This modification severely influenced this prototype' s 28% isentropic efficiency. The highest isentropic and volumetric efficiencies that were reported were 42% (at 1800 rpm) and 68% (at 2200 rpm), respectively, in the case of the second unmodified expander. Stosic et al. (2002) investigated the use of a twin screw combined compressor and expander for a high temperature transcritical CO2 refrigeration systems. They stressed the need to reduce bearing loads as this would make the expandercompressor device more applicable to a larger range of pressures. They achieved a 20% reduction in the bearing load by balancing the loads of the compressorexpander rotors. They also concluded that throttling losses much larger than those associated with conventional refrigerants exist in this helical type turbomachine. They reported an idealized 72% increase in the coefficient of performance when applying this compressorexpander device to a high temperature transcritical CO2 refrigeration cycle. Hays and Brasz (2004) experimentally investigated the use of a turbinecompressor mechanism in a 6 ton transcritical CO2 refrigeration or liquefaction cycle. The axial flow turbine previously presented in Hays and Brasz (1996) as a twophase expander is used to drive a compressor in a hermetic turbinecompressor unit. At a rotational speed of 10,000 rpm the turbine and compressor had efficiencies of 69 and 80% respectively. The turbine had a measured efficiency of 56% at its maximum speed of 12,800 rpm. The vapor exiting the evaporator is then compressed in the turbinecompressor mechanism. The dual effects of expansion and partial compression in the turbinecompressor mechanism increased the system coefficient of performance by 39%. Driver (1996) theoretically described the potential of utilizing a compressorexpander device in a vapor compression system. Driver and Davidson (1999) have developed and tested a hingedvane compressorexpander unit for transcritical CO2 CyClCS. They found that if the compressorexpander device operated at a 100% isentropic efficiency, which is highly unlikely, a COP improvement of 40% could be realized when compared with a conventional heat pump. The investigators pointed out that their compressorexpander device would not work with refrigerants such as R134a because of sizing issues. Preissner (2001) investigated the use of scroll expanders in a transcritical CO2 cycle. The author also performed an experimental comparison of a conventional R134a and transcritical CO2 refrigeration cycles employing suction line heat exchangers. He found that CO2 CyClCS falls short in performance by 8 and 23% for a range of typical operating conditions with particular emphasis on medium to high outdoor temperatures. With the implementation of a scroll expander the cycles have an identical coefficient of performance at a condensing temperature of 25oC. At higher condensing temperatures though, he found that a significant performance gap exists in favor of the R134a cycle. The author found internal leakage losses to be the most significant loss mechanism due to limitations in machining accuracy and geometric design. The expander was thus not implemented in the cycles. Li et al. (2000) investigated the use of a vortex tube expansion device in a transcritical CO2 refrigeration cycle. The vortex tube's energy separation effect, known as the RanqueHilsch effect, separates the high pressure gas entering the vortex tube into two low pressure streams one at a low temperature and the other at a high temperature. The authors compared this expansion device to a reciprocating piston expansion device already developed by the authors. They concluded that an increase in the system coefficient of performance of 20% could be achieved if the piston expander's isentropic efficiency was 50%. The vortex tube expander' s isentropic efficiency would have to be on the order of 38% to achieve the same performance gain. Heyl et al. (1998) developed a free piston compressorexpander unit to be employed in a transcritical CO2 cycle. They found that because of the "fullpressure principle" a work extraction of 78% in relation to a complete expansion is obtained. Ertesvag (2002) described the geometry and thermodynamics of a patented rotarypiston machine that can be used as a compressorexpander device invented by K. Vading. He mentioned the possible use of this concept in vapor compression systems. Gas Refrigeration Cycles and Cryogenics The investigation of the use of expanders in gas refrigeration and cryogenic liquefaction cycles has been investigated by Gnutek (1979), Gnutek and Kalinowski (1986), and Baron and Trembley (2003). Gnutek (1979) analytically investigated the use of a rotaryvane expander in cryogenic liquefaction and vaporcompression gas refrigeration systems. The van der Waal's equation of state was used to determine the thermodynamic properties of the gas and therefore determine the performance of this expander device. The effects of friction, internal leakage losses and heat transfer from the ambient have been taken into consideration. Gnutek and Kalinowski (1986) described the use of a twostage rotaryvane compressor and a singlestage rotaryvane expander in a gas refrigeration unit using air as the working fluid. The authors obtained a 98oC evaporating temperature. Analytical equations are presented to describe the performance of the expander. The authors conclude that a gas refrigeration system employing a rotaryvane expander and compressor would be significantly smaller in size than that utilizing a reciprocating piston compressor and expander. The work extracted from the expander was coupled to a generator. Baron and Trembley (2003) investigated the use of indirect heat exchange and a turbo expander in a cryogenic refrigerator using liquid nitrogen as the refrigerant. According to the authors, heat transfer to the boiling liquid nitrogen is critical in cryogenic applications in order to ensure that the latent heat of vaporization is maintained as high as possible. The authors theoretically found that an expander whose isentropic efficiency is 75% can increase the amount of heat transferred to the liquid nitrogen by 28%. The authors discussed the pros and cons of using scroll and rotaryvane type expanders. The authors selected a centrifugal turboexpander because of compactness and cost. The author' s estimated that a turboexpander should not exceed $10,000 in order to be economically viable. Expander Selection Although the concept of utilizing a compressorexpander device is appealing, it cannot be applied to vapor compression and heat pump systems for the following reasons: * The necessary builtin volume ratios of the compressor and expander are very different. The expander may have a volumeratio 78 times that of the compressor. * There is an issue pertaining to the unequal inlet volume flowrates, which are a direct result of unequal inlet densities. * Cavitation erosion and other complexities may arise from twophase expansion which is likely to affect the expansion efficiency and may also have a negative impact on the compression process and therefore greatly reduce the system COP. Baek et al. (2002) suggested that rotaryvane expanders have an exceptional potential being utilized as expansion devices in refrigeration systems. This may be the case because of the fact that they may be mounted on the compressor shaft for ease of work recovery and have relatively less complicated valve timing. Rotaryvane expanders are also capable of accommodating higher rotational speeds. This translates into higher fluid handling capacity and hence a more compact device. Together with the conclusions mentioned above by the different investigators, the potential of employing rotaryvane type expanders in conventional vapor compression systems/heat pumps is very promising. CHAPTER 3 PARAMETRIC ANALYSIS OF CYCLES Models for the following refrigeration cycles have been developed in FORTRAN90 utilizing REFPROP 7.0's R134a, R22, R12 and pure hydrocarbon property subroutines: * Ideal singlestage cycle (henceforward referred to as the base cycle) *A modified ideal singlestage cycle with an expansion device (the expansion device will henceforward referred to as ED) * Actual singlestage cycle with and without an ED * Ideal cycle with twostage compression and an economizer (henceforward referred to as the economizer cycle) * A modified ideal economizer cycle with an ED * Actual economizer with and without an ED * Ideal cycle with an internal heat exchanger (henceforward referred to as the IHX cycle) * A modified ideal IHX cycle with an ED Both the evaporating and condensing temperatures were varied for all 8 cases. The system COP, refrigerating efficiency, refrigerating capacity, and required input work were found to be greatly dependent on the operating conditions. It is of significant interest to calculate the percent differences (system COP, refrigerating capacity and required input work) for the cycles with and without expansion devices. Ideal Cycles This section will describe both the thermodynamic processes involved with the base, economizer and IHX refrigeration cycles and the results when these cycles are modified by the addition of a twophase expander as a throttle valve replacement. Base Cycle The single stage ideal vapor compression cycle is the simplest cycle and is the basis of most refrigeration and airconditioning technology. These cycles have been utilized in cascade refrigeration systems to achieve higher condensing or lower evaporating temperatures. A schematic of the base cycle is shown in Figure 31. Both the Ts and Ph diagrams are shown in Figures 32. The base cycle consists of four processes that take place in the four components shown in Figure 31. Both the condensing and evaporating temperatures, To and Te, are initially known since they are usually design variables. This allows the computation of the corresponding high and low saturation pressures, P, and Pe, of the cycle. The refrigerant at State 1 is ideally in a saturated vapor state (xl=1). The properties at State 1 can be determined from P1=Pe and xl=1. In the base cycle, the refrigerant vapor undergoes isentropic compression in the compressor and exits at State 2. The properties at this state are found utilizing the following assumptions: P2=P, and s2=S1. The superheated refrigerant then enters the condenser where it undergoes isobaric heat rejection. The exit, State 3, of the condenser is saturated liquid (x3=0). The properties at State 3 can be found by P3=P, and x3=0. The saturated liquid refrigerant is then throttled in an expansion valve. This is an isenthalpic process. The properties at State 4 are thus determined from h4=h3 and P4=Pe. In the case where an expansion device is utilized as a throttle valve replacement, the saturated liquid undergoes an isentropic expansion process. The properties at State 4' are thus determined from s4'=S3 and P4'=Pe. The two phase refrigerant then undergoes isobaric heat addition in the evaporator. The refrigerant is ideally saturated vapor at the exit of the evaporator. The coefficient of performance for the base cycle and the base cycle with an expansion device (assuming the work output from the expander is ideally coupled to the compressor) are defined by Equations (31) and (32), respectively coP, = n4 (31) q, h h4 C'OP, = (3 2) b,exp comp ex (h h)(4 h Economizer Cycle The economizer cycle is modified so that the compression and expansion processes are carried out in two stages. A liquid/vapor separator increases the cooling capacity of the cycle. A schematic of the Ts and Ph diagrams and cycle is shown in Figures 33 and 34, respectively. Both the condensing and evaporating temperatures, To and Te, are initially known since they are usually design variables. This allows the computation of the corresponding high and low saturation pressures, P, and Pe, of the cycle. The refrigerant at the evaporator exit, State 1, is saturated vapor. The properties at State 1 can be determined by xl=1 and P1=Pe. The saturated vapor then undergoes isentropic compression in the compressor. The properties at the 1st stage compressor exit, State 2, can be found by S2=S1 and P2=Pi, where Pi is the intermediate pressure of the cycle. Stoecker (1998) has stated that the optimum intermediate pressure in a twostage compression process can be determined by the following relationship The refrigerant at State 5, the condenser outlet, is saturated liquid. The properties at State 5 can thus be found from PS=P, and xg=0. The refrigerant is then either expanded by an isenthalpic process (h6=h5, P6=Pi) in the throttle valve or by an isentropic process in the expansion device (S6'=S5, P6'=Pi). The liquid (noted by f) and vapor (noted by g) are then separated. The vapor in the amount of x is fed into the inlet of the second compressor. The liquid in the amount of (1x) however is expanded again. The liquid refrigerant, at State 6f, is either expanded by an isenthalpic process (h7=h6f, P7=Pe) in the throttle valve or by an isentropic process in the expansion device (s7'=S6'f, P7=Pe). The twophase refrigerant then undergoes isobaric heat addition in the evaporator and is saturated vapor at State 1. State 3 remains to be determined. An energy balance of the two streams feeding into State 3 will determine the enthalpy at State 3 for the cases of isenthalpic and isentropic expansion processes as described by equations (34) and (35) respectively. h3 = 6h6g + 6 )h2 (3 4) h3 X6'h6'g + 1 6')h2 (35) The properties at State 3 can then be determined from h3 and P3=Pi. The refrigerant at State 3 then undergoes isentropic compression in the second compressor. The properties at State 4 can then be determined from s4=S3 and P4=P,. The coefficient of performance for the economizer cycle and the economizer cycle with an expansion device (assuming the work output from the expander is ideally coupled to the compressor) are defined by equations (36) and (37), respectively CO%, = (36) COP econ, exp W +W W W comp,1 comp,2 exp,1 exp,2 (37) COP (x hh) con"'"exp 6,)>(h2 h)>+(h4 h3) (h, h6~ 1 6, >h6'f h,,) Internal Heat Exchanger (IHX) Cycle The internal heat exchanger (IHX) cycle is also known as the liquidtosuction heat exchanger (LSHX) cycle. This cycle incorporates a heat exchanger that subcools the saturated liquid leaving the condenser and superheats the saturated vapor leaving the evaporator. A schematic of the IHX is shown in Figure 35. Both the Ts and Ph diagrams are also shown in Figures 36 respectively. Both the condensing and evaporating temperatures, To and Te, are initially known since they are usually design variables. This allows the computation of the corresponding high and low saturation pressures, P, and Pe, of the cycle. The analysis of the IHX cycle begins with the determination of States 3 and 6. The refrigerant is saturated vapor at the exit of the evaporator. The state properties may be determined from X6=1 and P6=Pe. Upon the refrigerant exiting the condenser, State 3, it is saturated liquid. The properties at this state point may be determined by x3=0 and P3=P,. The effectiveness of the internal heat exchanger is defined as follows q,, T T7 &,,= ct 1 (38) max T, T, For the case of the ideal cycle, the effectiveness is assumed to be equal to unity. This allows for the calculation of the temperature at State 1 (T1=T3). Using T1 and P1=P, the other state properties may be determined. State 4 may be determined by performing an energy balance on the IHX, assuming the mass flow of refrigerant and the specific heat of the refrigerant are both constant, as follows qn,4 = q6>1 7 6 = 3 4 (3 9) In the case of effectiveness equal to unity, T4= T6, the properties of the refrigerant at State 4 can be determined from T4 and P4=P,. The superheated vapor at State 1 undergoes isentropic compression in the compressor and exits at State 2. The properties at State 2 can be determined by S2=S1 and P2=P,. The subcooled liquid at State 4 can either be put through isenthalpic expansion in the expansion valve (h5=h4, P5=Pe) or isentropic expansion in the expansion device (sg'=s4, P5'=P4). The twophase refrigerant then undergoes isobaric heat addition in the evaporator and exits as saturated vapor at State 6. The coefficient of performance for the IHX cycle and the IHX cycle with an expansion device (assuming the work output from the expander to be ideally coupled to the compressor) are defined by equations (310) and (311) respectively q, h6 h, C'OPH 0 (310) w,, h, h q, h6 hs, COP "e (311) IHXex com ex h h4h For the base cycle configurations (with and without an ED) at a constant condenser temperature (25oC), the percent increase realized in the system COP was 8% to 19%, while an increase of 0.5% to 3.4% in refrigerating capacity was realized. The evaporator temperature was varied from 12oC to 10oC. The required work input to the compressor was found to decrease by 7.5% to 16%. For higher condenser temperatures, the percent differences in the system COP were found to increase by 1021%, 1324%, 1527% and 1830% for condensing temperatures of 30oC, 35oC, 40oC and 45oC, respectively. Actual Cycles The primary models: (1) simple vapor compression cycle; (2) vapor compression cycle with an economizer; and (3) vapor compression cycle with an internal heat exchanger, have been further modified to include the isentropic efficiencies of both the compressor and expansion devices. The effects of superheating, subcooling and pressure drops (both in the line and in the heat exchangers) as well as the effectiveness of the heat exchangers have also been considered. These effects would help achieve a more practical system model. For the actual base cycle system configurations (with and without an ED) and the case of constant condensing temperature (25oC) and varying evaporating temperature (12oC to 10oC), the percent increase realized of the system COP was 3.4% to 8.9%, while an increase of 0.2% to 1.7% was realized in terms of the refrigerating capacity. The required work input to the compressor was found to decrease by 3.3% to 7.2%. For a compressor efficiency of 85%, an expander efficiency of 50% and internal heat exchanger effectiveness of 70%, the values aforementioned are approximately half the values attained in the ideal case. The results for both the ideal and actual cycle improvements are presented in Table 31 and in Figures 37 to 313. It can be concluded from the preliminary results obtained that the maximum potential gain in the cycle coefficient of performance is obtained for the base cycle. This conclusion supports the work of Robinson and Groll (1998a) who found that the stream availability following the heat rej section process in the condenser is better utilized by an expansion device rather than an internal heat exchanger. Although improvements may be realized in the economizer cycle, the complexity and capitol cost of a twostage vaporcompression system hinder the utilization of this cycle with an expansion device. The following additional parametric inputs have been varied in order to determine the most important parameters when selecting the expansion device as well as the optimum operating conditions. Effect of Subcooling on System Performance The degree of subcooling that the refrigerant undergoes in or after the condenser is a key factor that affects both the power requirement and the refrigerating capacity of a vapor compression refrigeration cycle. Analysis of the effect of the degree of subcooling on the key system performance parameters including the refrigerant effect, expander workoutput and overall system COP has been done. An increase in the degree of subcooling was found to decrease the useful work output from the expander but increases the overall system COP by increasing the refrigerating effect. Figures 314 to 318 show the aforementioned trends. Among the most promising preliminary conclusions that may be drawn from this analysis is that cavitation erosion may be greatly reduced in the inlet of the expander since, depending on the degree of subcooling, the refrigerant entering the expander may only be liquid. Hence, vapor will only start to form when the refrigerant has experienced a sizeable pressure drop in the expander' s cavity (i.e. at large angular displacements). According to current literature, cavitation erosion in turbomachinery is prevalent at the inlet and the initial stages of compression and expansion due to the high velocity and composition associated with the incoming twophase flow. Effect of Superheating on System Performance The degree of superheat that the working fluid experiences in the evaporator is critical in a vapor compression refrigeration system to ensure that the working fluid leaving the evaporator is completely vapor. Besides the well documented benefits of better compressor performance and longer service life, the following figures (Figures 319 and 320) analyze whether the degree of superheat has any significant effect on the system COP, refrigerating effect and the net work input to the system. A similar parametric analysis, as in the case of condenser subcooling, reveals that the increase in the degree of superheat in the evaporator does not significantly increase/decrease the work input into the system nor increase the refrigerating effect produced by the system. For a large degree of superheat such as 90C, the gain in the refrigerating effect is roughly 5%. These results are presented in Figures 319 and 320. There exists however a tradeoff between the degree of superheat and the heat exchanger area required in order to achieve that superheat. Evaluation of CFC, HFC and Transcritical CO2 Refrigeration Cycles Vapor compression refrigeration research has been significantly influenced by the elimination of ozonedepleting refrigerants such as chlorofluorocarbons (CFCs), the planned phase out of partially ozonedepleting refrigerants such as hydrochlorofluorocarbons (HCFCs), and the interest in replacing what was once thought to be harmless refrigerants such as hydrofluorocarbons (HFCs). Among the frontrunners in replacing these refrigerants is carbon dioxide. A first and secondlaw based performance evaluation of conventional refrigeration and transcritical carbon dioxide systems is presented here. The working fluids investigated include R134a, R22 and R744 (CO2). The systems investigated include the basic and modified vapor compression systems. The modified system consists of a twophase expansion device that is employed as a throttle valve replacement. The irreversibilities of the different system components in the basic and modified systems are presented. Comparison of the potential increases in the refrigerating effect, reductions in the work required to operate the system and resulting increase in the system coefficient of performance are discussed. Comparison of the reductions/increases in cycle irreversibility and component contributions due to the employment of an expansion device are also discussed. Key expander operational parameters, such as the process volume ratio, are investigated. A recent revival of carbon dioxide's use as a refrigerant has been given much attention in recently published literature. This arises from the need to replace ozone depleting CFCs and HCFCs and the global warming contributors HFCs. In comparison, carbon dioxide is naturally occurring and is thus an environmentally friendly refrigerant with an ozone depletion potential of zero. Published literature that discussed the revival of carbon dioxide's promise as a potential candidate to replace CFCs and HFCs includes those of Lorentzen (1994), Lorentzen and Pettersen (1993). Due to the low critical temperature of CO2 however, 30.98oC, the heat rejection process typically takes place at a supercritical temperature in a gas cooler cooled by ambient air. The critical pressure of CO2 is 7.3 8 MPa. This high heat rej section pressure requires a substantial increase in the compressor work required to achieve it. This dramatically decreases the system coefficient of performance. Another inherent theoretical limitation of the basic transcritical CO2 system is the fact that the refrigerant leaving the gas cooler may only be cooled to the ambient temperature. To overcome this, an internal heat exchanger may be utilized to provide a means of subcooling. In the case of a conventional vaporcompression system, subcooling is typically obtained by increasing the area of heat transfer of the condenser. It has been reported that the performance of transcritical CO2 Systems suggests that the technology is comparable to that of existing systems (Robinson and Groll, 1998). It has also been suggested that transcritical CO2 component technology must be optimized in order to meet the unique operational characteristics of carbon dioxide. This technology however differs significantly from conventional refrigeration systems (Kim et al. (2004)). Although the stateoftheart of transcritical CO2 Systems is still far from optimum, the inherent thermodynamic performance of the basic transcritical CO2 System must be comparable to existing refrigeration technology. The system coefficient of performance, regardless of the technology used, may be increased by the utilization of expansion devices, liquidtosuction (internal) heat exchangers or performing compression in multiple stages, to name a few. In particular, many researchers have concluded that the isenthalpic throttling process may be the largest source of irreversibility in a transcritical CO2 System. This section analyzes and compares the use of an expansion device as a throttle valve replacement in both conventional and transcritical CO2 Systems. There are two advantages to using expansion devices with output work. The first is the fact that lower enthalpy refrigerant is obtained at the inlet of the evaporator, which increases the refrigerating effect. The second is the extra work that can be extracted from the expansion process, which can then be used to lower the input power requirement of the compressor. The degree of potential increase of the system's coefficient of performance however is greatly dependent on the isentropic efficiency of the expansion device employed. Different expansion devices have been suggested in recently published literature. Reduction of irreversibilities associated with the expansion process also leads to an increase in the secondlaw efficiency of the system. The extent of these improvements in both conventional systems utilizing R22 and R134a as refrigerants and transcritical CO2 Systems are presented and discussed. An abundant amount of literature dealing with modified refrigeration systems that employ expansion devices exists. For the purpose of this section, only the most pertinent of those studies are examined. Robinson and Groll (1998) analytically investigated and compared the performance of a transcritical CO2 System and a conventional R22 refrigeration system with and without an expansion turbine. They found that the use of an internal heat exchanger along with an expansion device decreased the COP of the transcritical CO2 System by 68%. They concluded that the stream availability following the heat rejection process in the condenser is better utilized by an expansion device rather than an internal heat exchanger. They also found a 23% COP increase when comparing an R22 system and a transcritical CO2 System both with expansion devices with an isentropic efficiency of 60% and when the system is operated at evaporating and condensing temperatures of 5 and 50oC, respectively. They concluded that a conventional R22 system employing an expansion turbine outperforms all other systems including the transcritical CO2 System with an internal heat exchanger and an expansion turbine. Preissner (2001) investigated the use of a scroll expander in a transcritical CO2 System. He also performed an experimental comparison of conventional R134a and transcritical CO2 refrigeration systems employing suctionline heat exchangers. He found that the CO2 System's COP is 8 and 23% less than the R134a system for a range of typical operating conditions with particular emphasis on mediumtohigh outdoor temperatures. With the implementation of a scroll expander the systems were found to have an identical coefficient of performance at a condensing temperature of25oC. However at higher condensing temperatures a significant performance gap existed in favor of the R134a system. Preissner (2001) found internal leakage losses to be the most significant loss mechanism due to limitations in machining accuracy and geometric design. The expander was thus not implemented in either system. Componentlevel models are needed for the analysis of conventional and transcritical CO2 systems with and without an expansion device in place of a throttling valve. A general solution method has already been presented. Detailed componentlevel models that may include geometry, flow arrangement and loss mechanisms for the compressor, condenser, evaporator and expander may be developed separately and incorporated into this model when required. These componentlevel models will provide better estimates of the isentropic efficiencies of the compressor and expander as well as the heat exchanger size and effectiveness of the condenser and evaporator, respectively. In the analysis described here, R22, R134a and CO2 are aSSumed to be the working fluids. The thermodynamic properties of these fluids are provided by means of coupling REFPROP 7.0's (Lemmon, 2002) property subroutines with the models developed for this analysis. Pressure losses in all system components and throughout the system's piping have been neglected. Figure 31 shows a schematic of a conventional and transcritical CO2 refrigeration system with and without an expansion device. The two systems utilize a compressor, an expansion device and an evaporator. The only component that differs is the device by which heat is rej ected at the high pressure of the system. This component is a condenser in a conventional system and a gas cooler in the transcritical CO2 system. Figure 321 shows the Ts diagram of each system, respectively. Regardless of the refrigeration technology used, the required input work to compress saturated vapor at the evaporating pressure to superheated vapor at the pressure of heat rej section is w = (312) The isentropic efficiency re of the compressor takes into account irreversibilities such as internal leakage and friction. Kim et al. (2004) reported that although leakage and frictional losses associated with carbon dioxide compressors are lower, the current stateoftheart carbon dioxide compressor doesn't perform as well as a conventional refrigeration compressor. For the sake of comparison, isentropic efficiencies of current stateoftheart R22 and R134a compressors will be used to overestimate the performance of current CO2 COmpressor technology. This provides a technologyindependent evaluation of the performance of the two systems. Selection of the supercritical heat rej section pressure is another vital operational parameter that significantly influences the operation and performance of a transcritical CO2 System. Pressure is independent of temperature in the supercritical regime. According to numerous studies there exists a supercritical pressure at which the system' s coefficient of performance is maximum. Both graphical and numerical simulations have been proposed to select this heat rej section pressure (Kauf, 1999). For the purpose of this study, the heat rej section pressure is incrementally varied from the critical pressure (7.38 MPa) to 15 MPa until the optimum pressure at which heat rej section takes place is determined for various operating conditions. This procedure is performed for both basic and modified transcritical CO2 Systems. In the case of a conventional refrigeration system, the refrigerant undergoes de superheating, condensation and subcooling in the condenser. The effects of superheating and subcooling are considered when determining the heat exchanger effectiveness and the logarithmic meantemperature difference (LMTD). In the case of a transcritical CO2 System a gas cooler is employed to rej ect heat to the ambient and operates at a transcritical temperature and pressure. In an ideal gas cooler, the refrigerant temperature leaving the cooler, Te,out, would match the ambient temperature. The refrigerant enters the cooler as a vaporlike substance and leaves as a liquidlike substance. Following the conclusion of Robinson and Groll (1998) regarding the stream availability of the refrigerant leaving the cooler, no subcooling of the refrigerant is assumed. This allows for the maximum extraction of work during the expansion process. The heat rej ected in the condenser or gas cooler can be calculated as follows qcod/g = h7 h? (313) where h2,a is the actual enthalpy of the superheated/supercritical vapor calculated by means of the compressor isentropic efficiency. The enthalpy h3 is the enthalpy of the refrigerant leaving the heatrej ecting device. For the purpose of this study the refrigerant in the transcritical cycle is assumed to leave the gas cooler at a trans critical pressure and temperature of T3= Tg,ou,=Tamb+5. In the analysis of the conventional system the refrigerant is assumed not to experience any subcooling. The state properties thus correspond to the enthalpy of the saturated liquid at the condenser saturation pressure. In this study the difference between the ambient temperature and the condensing temperature in the conventional system is assumed to be 15oC. In conventional and transcritical CO2 refrigeration systems a throttling/expansion valve is utilized to expand the refrigerant from the pressure of heat rej section to the evaporating pressure. This irreversible isenthalpic process may be replaced by the use of an expansion device that would ideally expand the refrigerant in an isentropic fashion. The potential increase in the system COP due to both the increase in the refrigerating effect and decrease in the cycle net work input have been studied extensively in recently published literature for systems that utilize conventional refrigerants and transcritical CO2 aS working fluids. Different positive displacement type expansion devices such as helicalscrew, scroll, rotaryvane and reciprocating piston have been investigated. In this analysis, the type of expansion device used is not specified. The type of device along with the geometrical and operational characteristics may be programmed in separate subroutines that may provide actual performance predictions and an accurate estimate of the expander' s isentropic efficiency. Depending on the inlet conditions to the expander the actual work output from the expander can be expressed as w, = r (h, h ,) (314) The use of expander work output can either be coupled to the compressor shaft or utilized to drive other auxiliary machinery or systems that may contribute other system improvements. This study considers only the alternative of increased cooling capacity brought on from near isentropic expansion and ideal coupling of the expander work to the compressor. The size of an expansion device is primarily a function of the builtin volume ratio of the expander. The expander should not only match (or be fairly similar to) the process expansion ratio for typical system operating conditions but should also minimize the amount of wasted power recovery due to pressure losses incurred during underexpansion. The process volume ratio is defined as the ratio of the specific volume of the refrigerant at the inlet of the evaporator to the specific volume at the outlet of the condenser/gas cooler. The expansion process in positive displacement expansion devices is comprised of the intake, expansion and the exhaust processes. The builtin volume ratio of an expander is defined as the ratio of the specific volume at the start of the exhaust process to the specific volume at the end of the intake process. In this study it is assumed that both the builtin and process volume ratios are identical and defined as follows r, = "*"'I (315) where 'va,,,in is the specific volume of the refrigerant after the expansion process (or at the inlet to the evaporator). Depending on the cycle analyzed, this state may correspond to an isenthalpic or nonisentropic expansion process. We will further assume that the degree of superheat the refrigerant experiences in the evaporator is assumed to be zero unless otherwise indicated. For a given set of operating conditions the degree of superheat has much more of an influence on the overall performance of the system. The refrigerant is thus assumed to be saturated vapor upon exiting the evaporator unless otherwise indicated. An energy balance of the evaporator yields q, =(4 h )(316) where h'4,a is the actual enthalpy of the refrigerant entering the evaporator determined by means of the isentropic efficiency of the expander. In the case of an unmodified cycle h'4,a WOuld be replaced by h4h=h3 The coefficient of performance is defined as a ratio of the desired output to the required input. In the case of a modified vapor compression system with an expansion device, the net work input (compressor work less expander work) is the required input to the system. For simplicity, the work extracted from the expander is assumed to be ideally coupled to the compressor. The COP is thus defined as COP = e"(317) we w A secondlaw based comparison of conventional and transcritical CO2 refrigeration systems is a far better comparison criterion. Exergy or availability analyses reveal how closely actual refrigeration cycles are to ideal cycles. An exergy analysis also reveals the largest source of irreversibilities in the system by singling out those components that are most irreversible. The availability of a flowing fluid stream neglecting both kinetic and potential energy is defined as IV = (h ho) To (s so) (318) The subscript 0 denotes a reference state at which the system's temperature and pressure are in equilibrium with its surroundings (To=303.15 K ). This state is said to have zero availability if all other energy forms relative to the surroundings are zero. The specific irreversibility of a steady flow device with heat transfer may be expressed as the difference between the reversible work and the actual work as follows I = wve wact ITn Wex,q 1 w (319) where q, and Tr are the specific heat transfer and the reservoir temperature at which heat is transferred to/from, respectively. The sign of q, depends on the direction of heat transfer. Utilizing Equations (3 18) and (3 19), the specific irreversibilities of the various components can be derived. The specific irreversibility of an adiabatic compressor may be written as follows Ic = 1 V2,a h haa)= T (s2a s,)(3 20) In the case of a conventional system, the specific irreversibility of the condenser is Icona V)odt1 = T, (s, sz,a) (h3 hz,) (321) whereas, for a gas cooler, Tr in Equation (321) is replaced by the ambient temperature, Tamb. I the ambient temperature is identical to the reference temperature this expression would reduce to the difference in availability of the entering and leaving streams. If the expansion process is performed using a throttling/expansion valve the specific irreversibility of that isenthalpic process is I = To s ,, s, (322) whereas in the case of utilizing an expansion device, the specific irreversibility is lexp 3 a a)=Trsa ss)(323) The specific irreversibility of the evaporator for both systems is levap 4. 1) 9ea oT S ~ s)+ (h, h) (324) A system' s total irreversibility is the sum of the irreversibilities associated with its four components. Irreversibilities resulting from pressure drops in the system's components and transfer lines have been neglected. Irreversibilities associated with heat transfer in the system's piping have also been neglected. Both first and secondlaw based evaluations of R22, R134a and transcritical CO2 refrigeration technology are critical for selecting appropriate technology suitable for a specific application. For this purpose, simulation models for basic and modified vaporcompression refrigeration cycles have been developed. The selection of the optimum heat rej section pressure is necessary to adequately compare transcritical CO2 Systems to conventional systems. Maximum system COP occurs at the gas cooler' s optimum heat rej section pressure. Figure 3 22 illustrates the variation of the system COP as a function of the heat rej section pressure for both basic and modified systems at evaporating temperatures of 268 and 273 K. The COP of the basic system can be seen as a near constant for heat rej section pressures greater than the optimum heat rej section pressure. This is not the case for the modified system since higher heat rej section pressures adversely affect the performance of the expansion device. For an evaporating temperature of 273K, it can be seen that the COP is maximum when the heat rej section pressure is 10.2 and 9.75 MPa for the basic and modified systems, respectively. For an evaporating temperature of 268K the optimum heat rej section pressures were found to be 10.35 and 9.75 MPa for the basic and modified systems, respectively. The optimum heat rej section pressure can be determined in a similar fashion for different evaporating temperatures and operating conditions. For all operating conditions investigated, the optimum heat rej section pressure has been assumed to be 10.2 MPa. Although the actual optimum heat rej section pressure may vary by as much as 5% over the entire range of evaporating temperatures investigated, the system COP deviates by as much as 1 and 1.7% for the basic and modified systems, respectively. For the sake of computational time this deviation may be assumed negligible. Irreversibilities associated with the heat rej section and expansion processes are the largest sources of irreversibility in basic transcritical CO2 Systems. Figure 323 illustrates the variation of the percent of cycle irreversibility associated with the heat rej section and expansion processes as a function of the heat rejection pressure for basic and modified CO2 Systems. For these operating conditions, the compressor and evaporator contribute approximately 1617 and 56% of the basic cycle' s total irreversibility, respectively. The compressor and evaporator contribute approximately 2227 and 910% of the modified system's total irreversibility, respectively. It can also be seen in Figure 323 that the throttle valve contributes 40 to 10% more to the system's total irreversibility when compared to the gas cooler at heat rej section pressures of 9 and 1 1.25 MPa, respectively. In contrast, the contribution of irreversibility from the gas cooler is approximately 2% less and 25% more at heat rej section pressures of 9 and 1 1.25 MPa, respectively. The average irreversibilities of the expansion and heat rej section processes are 24% lower and 12.5% higher when comparing the modified and basic transcritical CO2 Systems, respectively. Component irreversibilities corresponding to an optimum heat rej section pressure are unlikely to be minimum. From Figures 322 and 323 it can be seen that the optimum heat rej section pressure corresponds to a maximum system coefficient of performance and a median value of the system irreversibility. A firstlaw based analysis of R22, R134a and transcritical CO2 Systems is required to evaluate the thermodynamic performance of basic and modified refrigeration systems. Employing a twophase expansion device as a throttle valve replacement is the only modification made to the basic system. This allows for an unbiased comparison of the different refrigeration technologies. Figure 324 shows the variation of the coefficient of performance of basic and modified R 22, R134a and transcritical CO2 Systems as a function of the evaporating temperature. It can be seen that the COP of the cycles investigated increases with increased evaporating temperature. The values of system COP for the basic and modified R22 systems are higher than those of R 134 systems by as much as 6 and 0.6%, respectively. This maximum difference corresponds to an evaporating temperature of 30oC. For the range of evaporating temperatures investigated, it can be seen that the COP of the basic transcritical CO2 System is lower than that of R22 by 33 34% and that of R134a by 2934%. On the other hand, the COP of a modified transcritical CO2 system is lower than that of an R22 system by 17.522% and that of an R134a by 1821%. The COP of a modified transcritical CO2 System is still 4.29% less than that of a basic R22 system. The COP of a modified transcritical CO2 System is 2% higher and identical to that of a basic R 134a system operating at evaporating temperatures of 30 and 25oC, respectively. At higher evaporating temperatures, however, the COP of a transcritical CO2 System is as much as 9% lower than that of a basic R134a system. When compared to similar R22 and R134a technology, the performance improvements of a modified transcritical CO2 System, in comparison to the basic system, are greater. Figures 325, 326 and 327, may further support this result. Figure 325 shows the difference in COP between the basic and modified R22, R134 and transcritical CO2 Systems as a function of the evaporating temperature, respectively. It can be seen that the difference in COP decreases with increased evaporating temperature for all three systems. The decrease is not as rapid however for the transcritical CO2 System. As the evaporating temperature decreases, the modified CO2, R 134a and R22 systems outperform the basic systems by 2730%, 1023% and 918%, respectively. This increase in the COP can be attributed to an increase in the refrigerating effect and a decrease in the input work required to operate the system. The refrigerating effect is defined as the specific evaporator capacity. From Figure 326, it can be seen that as the evaporating temperature decreases, the differences in the refrigerating effect of the modified and basic systems increase from 514%, 1.27% and 1.39% for the CO2, R134a and R22 systems, respectively. From Figure 327, the decrease of the required input to the system can be seen to be dramatically different. The work extracted from the expansion process is ideally utilized in the reduction of the input work to the compressor. It can be seen that as the evaporating temperature increases, the difference in required input work to operate a transcritical CO2 System increases. For increasing evaporating temperatures, the reduction in input work can be seen to be 2231%, 14.59% and 18.510% for transcritical CO2, R22 and R 134a systems, respectively. When comparing the basic and modified systems, the sizable differences in the increase in refrigerating effect and reduction of input work of CO2 pOint to favorable thermodynamic characteristics of CO2 when compared to those of R22 and R134a. When dealing with modified systems, the most favorable operational characteristic of CO2 is the volume ratio of the expander. This operational variable discussed earlier determines the size and practical feasibility of employing a twophase expansion device as a throttle valve replacement. Figure 328 shows the variation of the expansion device' s volume ratio as a function of the evaporating temperature for CO2, R22 and R134a. As can be seen, there is a sizable difference between the volume ratios for the different working fluids. It can also be seen that the volume ratio decreases as the evaporating temperature increases since the specific volume at the evaporator inlet decreases as temperature increases. For the evaporating temperatures reported (5 to 20oC only), the volume ratio can be seen to decrease from 2.71.6, 12.36.2, and 20.810 for transcritical CO2, R22, and R134a cycles, respectively. Efficient expansion devices are necessary to justify the cost and performance improvement of modified refrigeration systems when compared to conventional technology. This result is evident in Figure 329, which shows the difference in COP of basic and modified CO2, R22 and R134a systems as a function of the expander' s isentropic efficiency. In the case of CO2, it can be seen that the improvement in the system COP increases in a much more dramatic fashion when compared to R22 and R134a systems. The increase in the system COP can be seen to be 10.533%, 619% and 517% for CO2, R134a and R22 systems, respectively. A secondlaw based analysis is needed to determine the irreversibilities of the various components and to determine the increases/reductions in irreversibilities associated with any system modification. Figure 330 illustrates the component irreversibilities of a modified R22 system as a function of the evaporating temperature. As can be seen, for the modified R22 system, the largest sources of irreversibility are the condenser and compressor. Employing an expansion device has greatly reduced the irreversibilities associated with the basic system's throttling process. Component irreversibilities for the basic and modified CO2, R134a and R22 systems at a specific operating condition are given in Table 32. The table shows that the irreversibilities associated with the throttling process are reduced by 50, 18 and 16.5% for modified CO2, R134a and R22 systems, respectively. Similar figures and tables may be generated for various operating conditions and system configurations. Figure 331 shows the percentage of system irreversibility due to the condensing process for basic and modified R22 and R134a systems as functions of the evaporating temperature. The percentage of system irreversibility associated with the gas cooler for both the basic and modified transcritical CO2 Systems are not included for clarity. It was found that the gas cooler' s contribution to the system irreversibility is fairly constant and averages 29.5 and 42% for the basic and modified transcritical CO2 Systems, respectively. The figure also shows that the percentage of the total system irreversibility associated with the condensing process increases with evaporating temperature and with the use of an expansion device for both R22 and R134a systems. This increase in irreversibility decreases with increased evaporating temperatures from 106% and 116% for R134a and R22 systems, respectively. Figure 332 shows the percentage of system irreversibility associated with the expansion process for basic and modified CO2, R134a and R22 systems. As can be seen, the percentage irreversibility due to expansion is on average 47.5 and 24% for the basic and modified transcritical CO2 Systems, respectively. An average value of 50% reduction in irreversible losses due to the addition of an expansion device is expected with increasing evaporating temperatures. Irreversibilities associated with the expansion process in R134a and R22 systems decrease with increased evaporating temperature and may be reduced from 2411% and 2210.5%, respectively. The ratio of the total system irreversibility to the heat rejection rate yields a dimensionless system irreversibility that may be used to evaluate and compare the total system irreversibilities of transcritical CO2, R22 and R134a systems. The heat rej section rate has been used to non dimensionalize the total system irreversibility since the only difference between conventional and transcritical refrigeration technology is the heat rej section device. Figure 333 shows the variation of this dimensionless quantity as a function of evaporating temperature for basic and modified CO2, R22 and R134a systems. As can be seen, the basic and modified transcritical CO2 Systems have the largest dimensionless cycle irreversibilities associated with them. Modified R22 and R134a systems, on the other hand, have the least. The basic CO2 System and the basic R22 and R134a systems have fairly close dimensionless cycle irreversibilities. Theoretical simulation models have been developed to analyze and evaluate the first and secondlaw based performance of basic and modified R22, R134a and transcritical CO2 vapor compression refrigeration systems. The use of a twophase expansion device as a throttle valve replacement is the only modification made to the basic system. This allows for an unbiased comparison of the different refrigeration technologies. The following conclusions can be made: * The optimum heat rej section pressure corresponds to a maximum system coefficient of performance and a median value of system irreversibility. For the operating conditions investigated, the optimum heat rej section pressure of a modified system is on average 5% lower than that corresponding to a basic transcritical CO2 System. * The COP of basic and modified transcritical CO2 technology is inferior when compared to basic and modified R22 and R134a systems. The COP of basic and modified transcritical CO2 Systems are 29 to 34% and 17.5 to 22% lower than R22 and R134a systems, respectively. * Modified transcritical CO2 Systems can compete with basic R22 and R134a technology at lower evaporating temperatures but perform about 9% less at higher temperatures. * Favorable thermodynamic characteristics of CO2 are apparent when comparing the relative increases in COP and refrigerating effect and the reduction in input work to R22 and R 134a. For the range of evaporating temperatures investigated, the improvement in the CO2 system COP is 12 to 18% when compared to R22 and R134a systems. An increase of 3.8 to 7% in refrigerating effect and a 7.5 to 22% decrease in input work were also realized when compared to R22 and R134a systems. * The most favorable operational characteristic of CO2 is the volume ratio of the expander needed to expand the refrigerant to the evaporating pressure. At an evaporating temperature of SoC the volume ratio of an R22 and R134a expander are 4.5 and 7.7 times that of a CO2 expander, respectively. * Efficient expansion devices are necessary to justify the cost and performance improvement of modified refrigeration systems when compared to conventional technology. When compared to inefficient expansion devices (nexp=25%), efficient expansion devices (rexp 85%) may increase the system COP by 33%, 19% and 17% for CO2, R134a and R 22 systems, respectively. * The throttling process is the largest source of irreversibility in basic transcritical CO2 systems and the second largest in basic R22 and R134a systems. Irreversibilities may be reduced by as much as 50, 24 and 22% for modified CO2, R134a and R22 systems, respectively, employing a 65% efficient expansion device. * The basic and modified transcritical CO2 Systems have the largest total irreversibilities associated with them when compared to R22 and R134a systems. Performance and Size Optimization of Compression Refrigeration Systems A parametric analysis of key system operational variables in a modified vapor compression refrigeration system is presented in this section. A highly nonlinear relationship is found to exist between the many factors that influence the optimization of the system' s coefficient of performance and the associated size and weight of a refrigeration system. Of these factors, the degree of subcooling that the refrigerant experiences in the condenser is the most influential. It is the degree of subcooling that determines the necessary area of the heat exchanger required, ultimately affecting the size and the weight of a refrigeration system. The degree of subcooling also influences the size of the expander required to expand the refrigerant from the condenser pressure to the evaporator pressure. As the degree of subcooling increases, the resultant ratio between the outlet and inlet specific volumes decreases, and hence the builtin volume ratio of the expander would decrease. A decrease in the latter causes a reduction in the expander size and weight. As the degree of subcooling increases, the useful power output of the expander (which may be coupled to the compressor) decreases. On the other hand, this causes the enthalpy of the refrigerant entering the evaporator to decrease. This causes an increase in the refrigerating effect of the system. The extent of the influence of these competing effects on the system's coefficient of performance needed further analysis. This was done using a simulation code developed for that purpose. An optimum degree of subcooling exists where the coefficient of performance of the system is a maximum and the size and weight of the system are a minimum. It is recognized that the performance and compactness criteria may not be optimized simultaneously by a single subcooling choice. Furthermore, the penalties associated with the increase of the heat exchanger area and the decrease of power output of the expander should be minimized, while the benefits of the increasing refrigerating effect and the decreasing volumetric ratio of the expander should be maximized. The quantifieation of the dependencies of the coeffieient of performance, size, and weight of a vaporcompression system on design choices such as the degree of subcooling are now presented. Component level models are needed for vaporcompression systems that utilize an expander in place of the conventional throttling valve. A general solution method may be applied to model and validate experimental data and/or data provided by the manufacturers. The method presented is also applicable to both simple and modified vapor compression systems. Detailed componentlevel models that may include geometry, flow arrangement and loss mechanisms for the compressor, condenser, evaporator and expander may be developed separately and incorporated into this model when required. These componentlevel models will provide better estimates of the isentropic efficiencies of both the compressor and expander as well as the heat exchanger size and effectiveness of the condenser and evaporator. In the analysis described in this section, R22 is assumed to be the working fluid. The thermodynamic properties of R22 are provided by means of coupling REFPROP 7.0's property subroutines with the model developed for this analysis. Pressure losses in all the system components as well as throughout the system's piping have been neglected. Figure 31 shows a schematic of a simple vaporcompression cycle with and without an expansion device as a throttle valve replacement. In general, the required input work to compress saturated vapor at the evaporating pressure to superheated vapor at the condensing pressure is given by Equation (312). The refrigerant undergoes desuperheating, condensation and subcooling in the condenser. The effects of superheating and subcooling are considered when determining the heat exchanger effectiveness and the logarithmic meantemperature difference (LMTD). As a base case for comparing the effect of subcooling on system size and performance, the refrigerant leaving the condenser is assumed to be saturated liquid (i.e. no subcooling in the condenser). This represents the minimum heat exchanger area required to condense the refrigerant to a saturated liquid state and allow for the completion of the refrigeration cycle. When subcooling is accounted for, the present analysis only investigates the subcooling that the refrigerant experiences in the condenser resulting from an increase in the heat exchanger area. Other subcooling methods such as utilizing a liquidtosuction heat exchanger or using integrated or mechanically dedicated subcooling loops are not analyzed in this study. The heat rej ected in the condenser can be calculated as follows qcond (h2,a hj) (325) where h2,a is the actual enthalpy of the superheated vapor calculated by means of the compressor isentropic efficiency. The enthalpy h3 is the enthalpy of the refrigerant leaving the condenser. In the base case this corresponds to the enthalpy of the saturated liquid at the condenser saturation pressure. In cases of subcooling this corresponds to the enthalpy of the subcooled refrigerant determined at the saturation pressure of the constanttemperature condensing process and the temperature of the subcooled refrigerant. The effectiveness of the condenser is generally a function of the heat exchanger geometry, construction material and surface area. The effectiveness of condensers and evaporators however is independent of flow arrangement since the refrigerant undergoes an isothermal phase change process. The effectiveness of the condenser is thus defined as Co (T T ) cond,out c""n (3 26) mm~ C, conrdonr can, In the case of a condenser, the refrigerant typically has a very high heat capacity because it is undergoing phase change. The coolant, on the other hand, experiences the maximum temperature difference and therefore its heat capacity is equal to the minimum heat capacity, Cmm, = Co In this case, the temperature of the coolant leaving the condenser, Te,out, can be calculated as follows Tc,ou, = Tc,an + Econd Tcond,, n Tc,zn) (3 27) The relative size of the heat exchanger is calculated from the following Equation ~icond \ I Acond Im (A} A (328) where ATim is the logarithmic mean temperature difference, which is defined as follows (To T )(Tcond T) ATm = ond,out can onl n c,out (3 29) In( 7ond,out c a,,nd~nT~, Equation (329) is applicable to any heat exchanger flow arrangement since the refrigerant undergoes a phase change process (i.e. correction factor F=1) (Incorpera 2002). In typical vapor compression refrigeration systems a throttling/expansion valve is utilized to expand the refrigerant from the condensing pressure to the evaporating pressure. This irreversible isenthalpic process may be replaced by the use of an expansion device that would ideally expand the refrigerant in an isentropic fashion. The potential increase in the system COP due to both the increase in the refrigerating effect and decrease in the cycle net work input have been studied extensively in recent literature for systems that utilize conventional refrigerants and transcritical CO2 aS working fluids. Many different positive displacement type expansion devices such as helicalscrew, scroll, rotaryvane and reciprocating piston have been investigated. Here the type of expansion device used is not specified. The type of device along with the geometrical and operational characteristics may be programmed in separate subroutines that may provide actual performance predictions and an accurate estimate of the expander' s isentropic efficiency. Depending on the degree of subcooling the refrigerant experiences in the condenser, the inlet conditions to the expander may be determined assuming that subcooling in the condenser occurs at a constant pressure. The actual work output from the expander can be expressed as w, = Fl(h, h ) (330) The size of an expansion device is primarily a function of the builtin volume ratio of the expander. The expander should not only match (or be fairly similar to) the process expansion ratio for typical system operating conditions, but should also minimize the amount of wasted power recovery due to pressure losses incurred during underexpansion. The process volume ratio is defined as the ratio of the specific volume of the refrigerant at the inlet of the evaporator to the specific volume at the outlet of the condenser. This volume ratio is expected to be smaller when the refrigerant leaving the condenser is subcooled. The complete expansion process in positive displacement expansion devices is comprised of the intake, expansion and the exhaust processes. The builtin volume ratio of an expander is defined as the ratio of the specific volume at the start of the exhaust process to the specific volume at the end of the intake process. In this study it is assumed that both the builtin and process volume ratios are identical and defined as z; = "*"'11 (331) cond out We will further assume that the degree of superheat the refrigerant experiences in the evaporator is zero unless otherwise indicated. For a given set of operating conditions, the degree of superheat has much more of an influence on the overall performance of the system. In this study, the impact of the degree of subcooling on the expander cycle performance and size is of primary interest. The refrigerant is thus assumed to be saturated vapor upon exiting the evaporator unless otherwise indicated. An energy balance of the evaporator yields qeve, = (h, h ,) (332) where h'4,a is the actual enthalpy of the refrigerant entering the evaporator determined by means of the isentropic efficiency of the expander. The COP is thus defined as COP = e"(333) we w The results presented here are in terms of dimensionless quantities. This allows the reader to capture general trends of the analysis without the distraction of system specific calculations. The dimensionless groups that will be extensively used in the presentation of the results are defined as follows SCOP Dimensionless COP: COP* (334) Dimensionless expander work output: w, xp exp (3 3 5) exp,reference Dimensionless expander volume ratio: r; = r' (336) fUA\*UA Dimensionless condenser capacitance: = m UAz~ iz1vfeec (337) For a vaporcompression system of known refrigerating capacity both the overall heat transfer coefficient, U, of a condenser with a constant effectiveness and the mass flowrate of refrigerant may be assumed constant. The condenser capacitance can thus be considered a direct measure of the heat exchanger area required to reject a given heat load in the system's condenser if these two conditions are met. A constant cooling capacity comparison criterion may also be used to constrain the analysis presented here. In the constant cooling capacity design scenario, the mass flowrate of refrigerant through the system would vary depending on the degree of subcooling which will ultimately reduce the system component and pipe sizing. The reduction in system size and weight would be significantly less, however, than that achieved by reducing the heat exchanger area. Figure 334 shows the variation of dimensionless condenser capacitance, expander volume ratio, expander work output and system COP as functions of the dimensionless refrigerating effect. In this case, the refrigerant does not experience any subcooling in the condenser. The refrigerating effect is defined as the difference in the specific enthalpy of the refrigerant at the exit and the inlet of the evaporator. For a given condensing temperature, the refrigerating effect increases as the evaporating temperature increases. The data used to plot Figure 334 has been normalized by the refrigerating effect corresponding to the lowest evaporating temperature analyzed. It can be seen from Figure 334 that as the refrigerating effect increases (for instance due to an increase in the evaporating temperature) the system COP increases dramatically. This is due to the fact that as the difference in operating temperatures (or pressures) decrease both the compressor input work required and expander work output decrease. For the operating temperatures reported, the compressor work input decreases by 74%, while the expander work output decreases by 84%. Furthermore, for the same temperature range, an increase in the refrigerating effect of 7.5% is observed. This results in an increase in system COP of about 75% when compared to a system operating at the lowest evaporating temperature analyzed (223 K). As the refrigerating effect increases, both the size and work output of the expander decrease. As mentioned earlier, the expander work output decreases by about 84% whereas the expander volume ratio decreases by 92%. As the evaporating temperature increases, the benefits of utilizing an expander as a throttle valve replacement become less significant. The condenser capacitance increases with the increase in the refrigerating effect. Over the full range of the refrigerating effect considered, the condenser capacitance can be seen to increase by 27%. Figure 335 shows the variation in the dimensionless expander volume ratio and work output as functions of the evaporating temperature for different degrees of subcooling in the condenser. The expander volume ratio and work output decrease with an increase in the evaporating temperature and the degree of subcooling. At an evaporating temperature of 278 K, typical in airconditioning applications, the expander volume ratio is found to be 8% and 16.4% less than the volume ratio corresponding to the case of no subcooling in the condenser for a degree of subcooling of 4oC and 8oC, respectively. The expander work output was found to be 15.3% and 29% less than the work output corresponding to the case of no subcooling in the condenser for a degree of subcooling of 4oC and 8oC, respectively. Figure 336 illustrates the variation in the dimensionless condenser capacitance as a function of the evaporating temperature for different degrees of subcooling in the condenser. It can be observed that as the degree of subcooling increases, the variation in the condenser capacitance increases dramatically. For a typical airconditioning evaporating temperature of 273 K the condenser capacitance is found to be 24.6% and 54.3% greater than that corresponding to the case of no subcooling in the condenser for a degree of subcooling of 4oC and 8oC, respectively. As previously mentioned, there exists a direct correlation between the heat exchanger area and the condenser capacitance. The increase in the heat exchanger area appears to be much larger than the decrease in the expander volume ratio and work output. The effects of system variables such as the isentropic efficiencies of the compressor and the expander, and the condenser' s effectiveness on the system COP, condenser capacitance, expander volume ratio and work output are discussed below. Figure 337 shows the variation of the dimensionless condenser capacitance as a function of the degree of subcooling for different values of the condenser' s effectiveness. The operating conditions and system variables are listed below Figure 337. For the case of no subcooling, the capacitance was found to be 25% and 56% larger for an effectiveness of 0.75 and 0.85, respectively, when compared to a system whose condenser has an effectiveness of 0.6. This results from the fact that as the effectiveness increases, the exit coolant temperature, Te,out, also increases, resulting in a decrease in the condenser's LMTD. For a constant condenser heat load, this leads to an increase in condenser capacitance. This increase is attributed to the increase of the heat exchanger effectiveness and does not take into account the increase in the heat exchanger area required to produce subcooling. This increase in condenser capacitance may result from either an increase in the overall heat transfer coefficient or an increase in the condenser' s area. For a condenser effectiveness of 0.6 it is found that the capacitance must increase by 13% and 29.5% in order to produce a degree of subcooling of 4oC and 90C, respectively. This represents an increase in the heat exchanger area of the same magnitude assuming that the overall heat transfer coefficient of the condenser and the mass flowrate of the refrigerant are constant. For an effectiveness of 0.85 it is observed that in order to produce a degree of subcooling of 4oC and 90C in the condenser, the capacitance must increase by 14.5% and 33%, respectively. The same trends are expected for different values of the ambient air temperature Tamb. Figure 33 8 shows the variation of the dimensionless expander work output as a function of the degree of subcooling in the condenser for different isentropic efficiencies of the expander. Detailed component level models of an expander would incorporate effects of friction and internal leakage losses and provide an accurate prediction of the expander' s isentropic efficiency. As it can be seen, the work output from the expander decreases with both the decrease in isentropic efficiency and increase of the degree of subcooling. For an ideal expander utilized as a throttle valve replacement it can be shown that a degree of subcooling of SoC and 10oC results in a decrease of the work output of the expander by 19% and 3 5%, respectively, when compared to the case of no subcooling in the condenser. Expanders whose isentropic efficiencies are 60% and 80% will theoretically produce less work than an ideal expander by that exact amount. An increase in the degree of subcooling in either case results in a decrease in the expander work output by 19% and 35% for a degree of subcooling of SoC and 10oC, respectively. From this figure it can be concluded that in order to make the use of an expander as a throttle valve replacement beneficial, losses that affect the expander' s isentropic efficiency as well as the degree of subcooling the refrigerant experiences in the condenser must be minimized. Figure 339 shows the variation of the expander volume ratio as a function of the degree of subcooling for different isentropic efficiencies of the expander. The expander volume ratio is found to increase as the isentropic efficiency of the expander decreases. Not only does the work output of the expander decrease, but also a larger expander adds both a weight and size penalty to the modified vaporcompression system. For the case of an ideal expander, a degree of subcooling of SoC and 10oC results in an increase in the volume ratio by 10% and 20%, respectively. When compared to an ideal expander, there exists a 1.67% and 3.33% increase in the volume ratio for the case of no subcooling in the condenser for expander isentropic efficiencies of 0.8 and 0.6, respectively. For a degree of subcooling of 10oC, this difference can be shown to decrease to about a 1.4% and 2.8% increase in the expander volume ratio for isentropic efficiencies of 0.8 and 0.6, respectively, when compared to an ideal expander. It is observed that the decrease in the expander work output is much more significant when compared to the increase in the expander volume ratio for both a decrease in the isentropic efficiency of the expander and the increase in the degree of subcooling the refrigerant experiences in the condenser. Figure 340 illustrates the variation of a system' s dimensionless COP as a function of the degree of subcooling for different isentropic efficiencies of the expander. It is observed that as the degree of subcooling increases, the COP also increases by 2%, 3.4% and 4.7%. This is the case for 10oC of subcooling in the condenser for expander isentropic efficiencies of unity, 0.8 and 0.6, respectively when compared to the case of no subcooling. For the latter case, the COP is found to be 1.7% and 3.4% lower than that corresponding to an ideal expander for expander isentropic efficiencies of 0.8 and 0.6, respectively. It may thus be concluded that the variation in COP is significant for larger values of subcooling in the condenser and then becomes more significant as the isentropic efficiency decreases. Figure 341 shows the variation of the dimensionless COP as a function of the degree of subcooling for different degrees of superheat in the evaporator. The system parameters are assumed constant and are listed below the figure. Superheating is beneficial to prevent compressor slugging. An increase in the degree of superheating is generally associated with an increase in the refrigerating effect and an increase in the input compressor work required to compress the superheated vapor to the condensing pressure. It is observed that as the degree of subcooling increases, the COP increases for all values of superheating analyzed. It is also noted that as the degree of superheat increases the COP is seen to decrease. This may be associated with a significant increase in the compressor input work in contrast to gains in the refrigerating effect. For the case of no subcooling in the condenser it may be shown that as the degree of superheat increases, the compressor input work increases by 2.8% and 5.3% whereas the refrigerating effect increases by 2.4% and 15.8% for a degree of superheat of SoC and 10oC, respectively. The degree of superheat has no direct impact on the performance or size of either the condenser or expander. The degree of superheat should be selected and minimized in order to maximize a given COP. The analysis presented in this section provides a foundation for applicationspecific optimization. The degree of subcooling the refrigerant experiences in a system's condenser has a significant effect on the size and performance of a vaporcompression system utilizing twophase expanders as throttle valve replacements. The Eindings of this analysis are as follows * As the evaporating temperature increases the benefits of utilizing an expander as a throttle valve replacement become less significant. This can be attributed to significant decreases in the expander volume ratio and work output. * The expander volume ratio and work output also decrease with increased condenser subcooling. * The work output from the expander decreases with both the decrease in isentropic efficiency and the increase of the degree of subcooling. Losses that affect an expander' s isentropic efficiency as well as the degree of subcooling must be minimized. * The decrease in the expander work output is much more significant when compared to the increase in the expander volume ratio for both a decrease in the isentropic efficiency of the expander and the increase in the degree of subcooling. * The variation in system COP is significant for larger values of subcooling in the condenser and become more significant as the expander's isentropic efficiency decreases. * The degree of superheat in the evaporator has no direct impact on the performance or size of either the condenser or expander. The degree of superheat should be selected and minimized in order to maximize a given system's COP. Pure Hydrocarbons as Refrigerants Hydrocarbons are very lucrative as refrigerant replacements for CFCs, HCFCs and HFCs since they are abundant, inexpensive and environmentally friendly because they have no ozone depletion potential. Among the maj or drawbacks of using hydrocarbons as refrigerants is their high flammability potential. This limits their use to hermetic systems and the slightest leak of a hydrocarbon refrigerant may prove to be catastrophic. The following is a review of recent literature pertaining to the use of hydrocarbons as pure refrigerants, in mixtures, and issues pertaining to flammability. The most promising potential hydrocarbons used as refrigerant substitutes are listed in the Table 33 along with pertinent fluid information. Many researchers have investigated the performance of pure hydrocarbons and hydrocarbon mixtures as refrigerants. According to Granryd (2001) several standards allow the use of hydrocarbons as refrigerants in internally safe, hermetically sealed systems with a charge limit of 0. 15 kg. This limits the use of hydrocarbons to domestic refrigerators and freezers and low capacity heat pumps. Larger refrigeration systems may utilize hydrocarbons as refrigerants as long as there is adequate exhaust and extreme safety precautions are in place. According to Granryd (2001) hydrocarbons are compatible with conventional materials used to construct vaporcompression refrigerating systems. Granryd (2001) theoretically investigated various cycle and heat transfer characteristics for various hydrocarbon refrigerants including propane, butane, isobutene, propene (propylene), cyclopropane, Dimethyl ether and a 50% propane50% isobutane mixture. The results were compared with cycle and heat transfer characteristics of R12, R22 and R134a. The author found that the pressure ratios associated with butane and isobutene are higher while propane and cyclopropane are lower than that of R22, respectively. The author also notes that in the case of using butane and isobutane as refrigerants, a necessary degree of superheat is required at the evaporator exit to ensure that isentropic compression doesn't move the vapor into the twophase region. When comparing the cycle coefficient of performance to the Carnot efficiency, butane was found to have the highest cycle Carnot efficiency. Granryd (2001) also experimentally investigated the use of propane in a refrigeration unit and compared its cycle performance with that of R12, R22, R134a and R152a. He concluded that a 35% increase in system COP and a 315% decrease in refrigerating capacity exists when propane is compared to conventional refrigerants. He attributed the decrease in compressor work to the lower molecular weight of propane. The use of pure hydrocarbons and mixtures as refrigerants in domestic refrigerators has been investigated by Hammad and Alsaad (1999), Jung et al. (2000), Tashtoush et al. (2002), Sekhar (2004) and Wongwises and Chimres (2005). Purkayastha and Bansal (1998) presented an experimental study of utilizing propane and a LPG mix (by mass fraction: 98.95% propane, 1.007% ethane and 0.0397% isobutane) as a suitable replacement for R22 in a heat pump. They found an increase in system coefficient of performance of 18 and 12%, and 9 and 4% for propane and LPG, respectively. These values correspond to condensing temperatures of 35oC and 55oC, respectively, at an evaporating temperature of 3oC. Colbourne and Suen (2004a, 2004b) appraised the flammability hazards of hydrocarbon refrigerants in refrigeration and heat pump systems. Dlugogorski et al. (2002) experimentally investigated the use of inerting agents with natural gas and a propanebutane mixture. Their recommendations however have not been tested experimentally in a refrigeration unit. In the case of pure hydrocarbon refrigerants the parameters under investigation include the system coefficient of performance, refrigerating effect, work consumption by the compressor and the effect of both subcooling and superheat on system performance. The case where an expander is utilized as a throttle valve replacement was also investigated. Comparisons with R12, R22 and R134a were also made to compare the performance of pure hydrocarbons as refrigerants in both the conventional and modified cycles. The results from these simulations are presented in Figures 342 to 347. Wexp L Wcomp Qin 4' 4 11 Te,Pe Figure 31. A schematic of the ideal base cycle (12341) and the modified base cycle with an expansion device (1234'1) s h Figure 32. Ts and Ph diagrams of the ideal base cycle (12341) and the modified base cycle with an expansion device (1234' Pc Pi Pe Te Ti To Figure 33. Ts and Ph diagrams of the economizer cycle (12345671) and an economizer cycle with an expansion device as a throttle valve replacement (123 456'7'1) Wcomp,2 Wcomp,1 Figure 34. A schematic of the economizer cycle (123 45671) and an economizer cycle with an expansion device as a throttle valve replacement (123456'7'1) comp IHX exp Figure 35. A schematic of the IHX cycle (1234561) and the modified IHX cycle with an expansion device as a throttle valve replacement (123 45'61) 3 For:4 32 31~6 T/Fr s h Figure 36. Ts and Ph diagrams of the IHX cycle (123 45 61) and the modified IHX cycle with an expansion device as a throttle valve replacement (123 45'61) Table 31. Summary of the percent changes in the system COP, refrigerating capacity and required work input by the addition of an expansion device for the ideal and actual R134a singlestage, economizer and IHX cycles Ideal*** Actual *,*** To, oC Evaporating Range ACOP, % AQe, % AWet, % ** ACOP, % AQe, % AWet, % ** 25 20"C to 10"C 818.7 0.43.4 7.615.9 3.48.3 0.21.7 3.37.2 30 20"C to 10"C 10.321.4 0.764.3 9.617.8 4.59.6 0.42.2 4.38.2 Base Cycle 35 20"C to 10"C 12.924.2 1.25.4 11.920 5.611 0.62.8 5.39.2 40 20"C to 10"C 15.627.1 1.86.7 1422 6.812.4 0.93.5 6.410.3 45 20"C to 10"C 18.530.2 2.48.2 16.524 8.214 1.24.3 7.511.4 25 20"C to 10"C 5.211 0.31.7 4.99 2.24.8 0.21.4 2.13.7 30 20"C to 10"C 6.512 0.52 6.110.2 2.95.6 0.41.7 2.64.1 Economizer 35 20"C to 10"C 8.114 0.72.6 7.411.4 3.56.4 0.52.2 3.24.6 Cycle 40 20"C to 10"C 9.615.5 13.2 8.812.7 4.37.3 0.82.7 3.75.1 45 20"C to 10"C 11.417.4 1.33.9 10.214.1 5.18.3 1.13.3 4.35.6 25 20"C to 10"C 2.63.6 0.140.6 2.53 1.62.9 0.10.6 1.52.4 30 20"C to 10"C 33.9 0.20.7 2.83.3 1.93.3 0.20.7 1.82.7 IHX Cycle 35 20"C to 10"C 3.44.5 0.31 3.233.7 2.33.7 0.20.9 2.12.9 40 20"C to 10"C 3.95 0.41.2 3.64 2.74.2 0.61.1 2.43.2 45 20"C to 10"C 4.45.5 0.61.4 44.4 3.14.7 0.51.4 1.73.5 *r,=85%, rexp=0.5, SIHX=0.7 ** a decrease in the amount of work needed theoretically *** maximum value corresponds to Te20"C and minimum value corresponds to Te=100C 2 0 2 4 6 8 10 Evaporating Temperature, oC B 30% n Base Tc=45C o Econom izer Tc=45C 25% O~ 20% 15% 0% 2 0 2 4 6 8 10 Evaporating Temperature, oC Figure 37. Variation of ICOP, between the modified cycle with an expansion device and the ideal cycle (R134a), with evaporating temperature for A) Tc=250C, B) Tc=450C for the base, economizer and IHX cycles  i 1 4% E1Base Tc=25C 12% rF +Economizer Tc=25C ~ HX Tc=25C 10% O 4% 2% 0%t 10% BW pet 'L~ cc~ .. :  E Tc=25C *Tc=30C 2 0 2 4 6 8 10 Evaporating Temperature, oC Figure 38. Variation of AQe and AWnet, between the ideal modified cycle with an expansion device and an ideal base cycle, with evaporating temperature for various condenser temperatures in a singlestage vaporcompression refrigeration unit (negative denotes a reduction). 5% o 5% S25% !  15 nTexo=0.7 10 5 I R134a, Ida nex,=0.75 0 ` + 22 Idea 202 81 Evaporating Tem perature, OC Figure 39. Variation of ACOP, between the modified cycle with an expansion device and the ideal cycle, as a function of the evaporating temperature for both R22 and R134a for various expander efficiencies Te=45oC (rcomp=85% when not ideal) 20% A Actual, Tc=25C 18% mActual, Tc=45C &Ideal, Tc=25C 16%~~ Ideal, Tc=45C 14% 8j 12% .9 10% 6% 0% 20 15 10 5 0 5 10 Evaporating Temperature, oC Figure 310. Variation ofABCOP, between the modified cycle with an expansion device and the ideal cycle, as a function of the evaporating temperature for various condenser temperatures for the actual and ideal cycle configurations of the economizer cycle. rcomp=85%, nexp=0.5 6% 5% 4% 3% % 2% ~Actual, Tc=25C mctual, Tc=45C 1% ~&deal, Tc=25C E1deal, Tc=45C 0% 20 15 10 5 0 5 10 Evaporating Temperature, "C Figure 311i. Variation ofA~COP, between the modified cycle w/ an expansion device and the ideal cycle, as a function of the evaporating temperature for various condenser temperatures for the actual and ideal cycle configurations of the IHX cycle reomp 85%, rlexp 0.5, SIHX=0.7 o 0.95 11ep 1 0.9 R22 0.85 0.8 0.75 11ex=0.75 2 O 2 4 6 8 10 Evaporating Temperature, oC Figure 312. Variation of refrigerating efficiency as a function of the evaporating temperature for both the base (no expander) and ideal and actual modified cycle with and an expander at a condenser temperature of To45oC 0.9 ncomp=85%, rexp=0.5, SIHX=0.7 0.8 S0.7 S0.6  ct Actual, IHX Cycle 0.5 Actual, Base Cycle Actual, Economizer Cycle 0.4 20 15 10 5 0 5 10 Evaporating TemperaturePo Figure 313. Variation of refrigerating efficiency as a function of the evaporating temperature for the actual base, IHX and economizer cycles with an expander at a condenser temperature of Te=25oC _,i is''   x   ....x x.xx = Tc= 25C St Tc=30C ....x Tc= 35C < aTc=40C  Tc=45C Figure 314. Variation of an ideal system's COP as a function of the degree of subcooling for various condensing temperatures (Te=5oC, ATsh=0 oC) Te=45oC  * To=250C  t Isenthalpic Expansion SIsentropic Expansion ATsubcooling, OC Figure 315. Variation of an ideal system's COP as a function of the degree of subcooling for various condenser temperatures and expansion processes (Te=5oC, ATsh=0oC) To= 450 C 160 c t~k Iethlic Epanion a 120 Te=25oCi'  Isentropic Exp~ansion 100 0 2 4 6 8 ATsubcooling, oC Figure 316. Variation of the refrigerating effect as a function of the degree of subcooling for various condenser temperatures and expansion processes (ATsh=0oC)  C sc, Isenthalpic 26  5C sc, isenthalpic 0C sc, Isentropic 5C sc, Isentropic .* 22 10 5 7 9 11 13 15 Evaporator temperature, oC Figure 317. Variation in an ideal system's COP with respect to the evaporator temperature for different degrees of subcooling and expansion processes (ATsh=0oC) 20 c c4" 15 OC 10 5C 10 5 7 9 11 13 15 Evaporator temnperature, oC Figure 318. Variation of the difference in system COP,%, between the ideal cycle and modified cycle with an expansion device as a function of the evaporator temperature for various condenser temperatures and degrees of subcooling (ATsh=0oC) 20 159.....~.....,...~ ,~~~~~,~~~~~,~~~~,~ ~~~,~~~~~g~~~~~ 10 ~ ~_ ~ _,_ _,_ _, ,_ _,_ _,_ _   Tc=25C oTc=35C 9 Tc= 45C Asuperheats oC Figure 319. Variation of the difference of the system COP, %, base cycle and modified cycle with an expansion device as a function of the degree of superheat in the evaporator for various condenser temperatures. 200 ha180 M 120 4T=5 A Tc=45C 100 0 2 T 4 oC 6 8 superheat, Figure 320. Variation of the refrigerating effect for an ideal cycle as a function of the degree of superheat for various condenser temperatures A B Figure 321. Ts diagram of the basic system (12341) and the modified system with an expansion device (1234'1) for a A) conventional refrigeration system and B) transcritical CO2 refrigeration system a Te=273 K Modified System A Te=268 K = Te=273 K Te=268 K 11.5 2.5 ct . Basic System 2? 10. 5 60 , 50 40 30 ~ 20 1 10 0 ..s..s' Modified System * _.r.a Basic system L ..  r   aGas cooler Valve  Gas cooler . ....Expander ycomp=0.85 rexp=0.65 T3= 313 K Tevap=273 K 11.5 9 9.5 10 10. 5 Heat Rejection Pressure, MPa Figure 322. Variation of system coefficient of performance as a function of heat rej section pressure for various evaporating temperatures for basic and modified transcritical CO2 Systems Heat Rejection Pressure, MIPa Figure 3 23. Percentage of cycle irreversibility associated with the heat rej section and expansion processes as a function of heat rej section pressure for basic and modified transcritical CO2 Systems .  Basic R744 System '.. ....M Modified R744 System B Basic R134a System SModified R134a Sy stem a Basic R22 System 43 5 EvapoatingTempeatur, O ~ Modified R22 System 1~,=0.85 S=0.65 0 5T =350C amb Tcon=500C T =400C gc_out Figure 324. Coeffieient of performance of basic and modified R22, R134a and transcritical CO2 Systems as functions of the evaporating temperature 35% R744 30% 25% 0 20% O <1 15% 10% 'I  .. ....  ..   R134a   R22 ne,=0.65 Tamb=350C Tcond= 500C Tooou=400C 30 25 20 15 10 5 0 5 Evaporating Temperature, OC Figure 325. Difference in coeffieient of performance between basic and modified R22, R134a and transcritical CO2 Systems as functions of the evaporating temperature 0.16 0.12 R744  R134a ....... R22 ycomp=0.85 rex=0.65 Tamb=350C Tcond= 500C Tgeou=400C 'r .. ~ S0.08 a,0.04 0 Evaporating temperature, oC Figure 326. Difference in refrigerating effect between basic and modified R22, R134a and transcritical CO2 Systems as functions of the evaporating temperature 0% S10% ...  comp=0.85 ~. 20%  ne,=0.65 ...Tamb= 350C Tcond= 500C 30% T cot= 40 oC 30 20 10 0 Evaporating Temperature, OC Figure 327. Difference in system input work between basic and modified R22, R134a and transcritical CO2 Systems as functions of the evaporating temperature (negative denotes a decrease) R1 34a ....... R744  R22 ycomp= 0.85 Tae=350C Tcond= 500C Tgeou=400C   35% 30% 25% 20% 15% 10% R744 R134a ....... R22 ncomp=0.85 Tamb= 350C Tcond= 500C T,,,o=400C Tap=C 85% 5% F  25% 45% 65% Evaporating Temperature, oC Figure 328. Volume ratio of the expander employed in modified R22, R134a and transcritical CO2 Systems as functions of the evaporating temperature Expander Isentropic Efficiency Figure 329. Difference in coefficient of performance between basic and modified R22, R134a and transcritical CO2 Systems as functions of expander isentropic efficiency   Compressor    Condenser SExpander  Evaporator ,,0.85 T,,=350C Tcond= 500C 40 r~30 ~20 10 Evaporating Temperature, oC Figure 330. Percentage of cycle irreversibility due to various components in a modified R22 system as functions of the evaporating temperature 50 A Basic R134a System 45 Modified R134a System "ji 40 .. x Basic R22 System E 35 p * ..* Modified R22 System 8 30 ...x..x ..=0.85 ..** De,=0.65 *0r 25  a ....'Tamb=350C o 20 a Tcond= 500C 30 20 10 0 Evaporating Temperature, oC Figure 331. Percentage of cycle irreversibility due to condensing process in basic and modified R22 and R134a systems as functions of the evaporating temperature m Basic R744 System . .. Moedified R744 System , Basic R134a System  A Modified R134a System X Basic R22 System  x Modified R22 System noo,=0.85 rex=0.65 Ta4=350C Tcond=500C Tgeou=400C 50 a 40 30 20 E 10 0 o E a > i: .. .  x ..  X.~X ~~ 20 10 0 Evaporating Temperature, O Figure 332. Percentage of cycle irreversibility due to the expansion process in basic and modified R22, R134a and transcritical CO2 Systems as functions of the evaporatmng temperature I Basic R744 System  4 Modif ied R744 System A Basic R134a System  M Modif ied R134a System H Basic R22 System  A Modif ied R22 System cop0.85 e=0.65 Tamb=350C Tcond=500C Too ot=400C 0.35 0.3 0.25 0.2 0.15 30 20 10 0 Eva porati ng Te mpe ratu re, og Figure 333. Dimensionless system irreversibility in basic and modified R22, R134a and transcritical CO2 Systems as functions of the evaporating temperature Table 32. Percentage of cycle irreversibility due to the various components in basic and modified R22, R134a and transcritical CO2 Systems Basic System Modified System R744 R1 34a R22 R744 R1 34a R22 Compressor, % 17.3 22.2 21.4 24.6 28.2 26.3 Condenser, % 33.6 38.1 42.6 46.7 Gas cooler, % 29.7  42.2 Expansion valve, % 46.5 33 29 Expander, %  23.2 14.6 12.5 Evaporator, % 6.5 11.2 11.5 10 14.6 14.5 condenser capacitance  expander volume ratio  expander w ork output COP 1.08 Figure 334. Variation of dimensionless COP, expander work output, expander volume ratio and condenser capacitance as a function of dimensionless refrigerating effect. Tcond= 450C, Tamb= 25"C, Econd=O 075, rcomp= 085, rexp=0 075 1.02 1.04 1.06 Dimensionless refrige rating effect Degree of Subcooling, oC 4 8 4 8 30 20 10 0 10 Evaporating tempe rature, oC Figure 335. Variation of dimensionless expander work output and expander volume ratio as a function of evaporating temperature for various degrees of subcooling in the condenser. Tcond=450C, Tamb=25"C, Econd=0.75, rcomp=0.85, rx=0.75 Degree of Subcooling, OC  4 8 0 10 Evaporating temperature, oC Figure 336. Variation of dimensionless condenser capacitance as a function of evaporating temperature for various degrees of subcooling in the condenser. Tcond=450C, Tamb=2500, Econd=0.75, rcomp=0.85, rp=0. 75 2.6 a 2.2 S1.4 Condenser effectiveness 0.6 0.75  0.85 Figure 337. Variation of dimensionless condenser capacitance as a function of degree of subcooling in the condenser for various values of condenser effectiveness. Tcond=450C, Tevap=50C, Tamb=25"C, comp=0. 75, r,=0. 75 ~~ ~~ Expander efficiency 1 0. 8 .0. 6 0.7 0.5 Figure 338. Variation of dimensionless expander work output as a function of degree of subcooling in the condenser for various expander efficiencies. Tcond450C Teva=50C, Tamb=3000, Econd=0.75, rcomp=0.85 Degree of subcooling, oC Degree of subcooling, OC 1.05 1 0.95 0.9 0.85 Expander efficiency 1 0. 8 .......0.6 10 0 2 4 6 8 Degree of subcooling, oC Figure 339. Variation of dimensionless expander volume ratio as a function of degree of subcooling in the condenser for various expander efficiencies. Tcond450C Teva=50C, Tamb=30"C, Econd=0.75, rcomp=0.85 1.04 0.96 Excpander efficiency 0.6 0.8 0.92 Degree of subcooling, oC Figure 340. Variation of dimensionless COP as a function of degree of subcooling in the condenser for various expander efficiencies. Tcond450C, Tevap 50C Tamb=30"C, Econd=O 075, rcomp= 085 Degree of superheat, OC 0 2 4 6 8 10 MW Toi oC Perit, perit3 "'' kPa kg/m' Butane (R600) 58.12 151.98 3796 227.84 Ethane (R170) 30.07 32.18 4872 206.58 Isobutane (R600a) 58.12 134.67 3640 224.35 Propane (R290) 44.1 96.675 4247 218.5 Propene (Propylene) (R1270)42.08 92.42 4664 223.39 1.04 1.02 0.98 Degree of subcooling, OC Figure 341. Variation of dimensionless COP as a function of degree of subcooling in the condenser for various evaporator degree of superheat. Tcond450C, Tevap 50C Tamb=25"C, Econd=0.75, rcomp=0.85, Texp=0.85 Table 33. Hydrocarbons viewed as potential refrigerants A B 400 350 Y"350 300 R134a S300 t~250 R2 S2501 R1 200 Butane 150 150 Isobutane a,100 Propane an100 E Proplyene S50 50 0 0 5 0 5 10 5 0 5 10 Evaporating Temperature, OC Evaporating Temperature, oc Figure 342. Variation of the refrigerating effect as a function of evaporating temperature for various refrigerants at a condensing temperature of A) 25oC and B) 45oC for the ideal base cycle A B 17 mR134a E 15 6  a, R22 0. 1 3 ~5 Butane Isobutane E Propane .2 4 $ 9 Proplyene 7 3 5 0 5 10 5 0 5 10 Evaporating Temperature, OC Evaporating Temperature, OC Figure 343. Variation of the ideal base cycle coefficient of performance as a function of evaporating temperature for various refrigerants at a condensing temperature of A) 25oC and B) 45oC 65 55  45  35  25  15 1( 5 0 5 1 Evaporating Temperature, oc R134a  R22  R12 Butane  Isobutane  Poay e 5 0 5 Evaporating Temperature, OC Figure 344. Variation of compressor work as a function of the evaporating temperature at a condensing temperature of A) 25oC and B) 45oC for various refrigerants in an ideal base cycle 28% 15% 14% 26% 13% R14 i0 lif 24% R2 eg 1 2% R12 p 22% 11% Butane O 2010 Isobutane S18% Propane Proplyene g! 1 6% 7% S1 4% 6% 5 0 5 10 5 0 5 10 Evaporating Temperature, oc Evaporating Temperature, OC Figure 345. Variation of the increase of COP (when comparing the base cycle and the expander cycle) as a function of the evaporating temperature for various refrigerants at a condensing temperature of A) 25oC and B) 45oC c go "G .5 > a * oe cn Qu 14% 1 3% 12%  11% _ 10% 9%  8% 7% 6%  5% 24% 2270 20% 18% 16% 14% 1 2% 1 0%  R1 34a  R22 R1 2 Butane  Isobutane Propane Proplyene 0 5 Evaporating Temperature, OC 10 5 0 5 Evaporating Temperature, OC Figure 346. Variation of the decrease in network (when comparing the base cycle and the expander cycle) as a function of the evaporating temperature for various refrigerants at a condensing temperature of a) 25oC and b) 45oC t 1.8% 1.5% S1.3% *C 0 1.0% C L e *C 0.8% c E 0.5%  o S 0.3% 02 .0%  R134a  R22 R12 Butane  Isobutane Propane Propylene 5 0 5 10  Evaporating Temperature, OC Evaporating Temperature, OC Figure 347. Variation of the increase in refrigerating effect (when comparing the base cycle and the expander cycle) as a function of the evaporating temperature for various refrigerants at a condensing temperature of a) 25oC and b) 45oC CHAPTER 4 MATHEMATICAL MODEL OF AN IDEAL ROTARYVANE EXPANDER Much literature has been reviewed in order to formulate an accurate and rigorous analytic thermodynamic and fluid model of a rotaryvane expander. Most of the literature found deals with rotaryvane expanders used predominantly in hightemperature applications where the working fluid is vapor (namely steam and R113) and is modeled using idealgas relations. This negates the many additional complexities that arise due to the necessary formation of vapor from liquid exiting the condenser in vapor compression cycles. These modeling complexities may include but are not limited to cavitational erosion, choking, issues dealing with lubrication, and a possible increase of friction and internal leakage losses due to significant variations in the density and viscosity of the twophase working fluid. In order to accurately model a twophase rotaryvane expander, the studies conducted in the existing literature must be revisited and modified accordingly to predict such parameters as the working fluid's pressure, temperature and mass variations as well as an overall estimate of power losses, volumetric efficiency, power output and torque of the rotaryvane expander. Literature Review of Modeling of Rotaryvane Expanders While literature dealing with modeling and design improvements of various types of compressors and expanders, such as helical screw, reciprocating piston, scroll, Wankelengines Badr et al. (1991a, 1991b, 1991c) and rotarypiston are abundant, this review is confined to rotaryvane (or slidingvane) type expanders and compressors, hence referred to as MVE and MVC, respectively. Smith et al. (1990, 1992) introduced the principles, operation and testing of a novel type compressor, the Groll rotaryvane compressor. They found a 19% and 15% increase in volumetric and adiabatic efficiencies, respectively when compared to a conventional rotaryvane compressor. There have not been any studies utilizing this as an expansion device. The positivedi splacement rotaryvane expander has been widely used for waste heat recovery in Rankine cycles. Badr et al. (1984) cited economics, ease of manufacturing and low maintenance as the most important parameters in the selection of a MVE as an expansion device. Among the investigators who developed mathematical models describing the geometry of rotaryvane type turbomachinery (compressors, expanders, pumps and airmotors) are Wolgemuth and Olson (1971), Marsters and Ogbuefl (1972), Badr et al. (1985a, 1985b), Somayajulu (1971), and BenBassat and Wolgemuth (1972). Mechanical friction in a MVE has been investigated by Beck et al. (1966), BenBassat and Wolgemuth (1972), Peterson and McGahan (1972), Badr et al. (1986a), Robertson and Wolgemuth (1978), and Edwards and McDonald (1972). Internal leakage losses in a MVE have been investigated by Peterson and McGahan (1972), Jacazio et al. (1979), Badr et al. (1985c), and Robertson and Wolgemuth (1978). All of the above studies either dealt with the expansion or compression of a working fluid (air, steam, and vapor) that could be modeled by the idealgas equation of state. The studies in question also dealt with rotaryvane type turbomachinery utilized as expanders in Rankine cycles as air motors or pumps. Table 41 summarizes the type of application, working fluid, analyses performed, and the type of losses accounted for. The extent and accuracy of their analyses is beyond the scope of this work. Model Development In order to accomplish this, five separate subroutines had to be constructed to accurately predict the aforementioned parameters. A simplified flow diagram of the main computer program that has been developed and a brief description, in subsequent sections, of the subroutines to be utilized is presented in Figure 41. Thermophysical Model NIST's REFPROP 7.0's refrigerant property subroutines are linked with the various models and are called whenever thermophysical data is required. The capability to both use pure refrigerants and common refrigerant mixtures allows the use of REFPROP's property subroutines no matter the refrigerant. There is also the capability to use of a user defined and customized mixture. Geometric and Kinematic Model In order to model the performance of a rotaryvane expander, the geometry of the expander and kinematics of the vanes must be accurately described mathematically. The basic geometrical and kinematic characteristics, as a function of the angular displacement of the expander' s rotor, are required to evaluate the performance of the expander. The parameters needed include: * Variation of the cell volumes * Volume expansion ratio, rv= V2/V1 (Figure 42) * Variations of the protrusions of the vanes outside their rotor' s slots * Vane's sliding velocity * Vane's accelerations A review of the literature reveals that many different models have been considered (Table 41). A primary difference among the models is accounting for the vane thickness. Many researchers have assumed an idealized vane thickness of zero when calculating the cell volume. For the purpose of this study, the expander is assumed to have a circular stator cylinder and the thickness of the vanes is taken into account initially. It can be shown from Figure 42 that a circular stator cylinder may be modeled as having two arcs (2n 6seat and 6seal) one of which is a sealing arc. The geometrical input parameters to the model and nomenclature used throughout this section are listed in Table 42 and are shown on a schematic of a circular expander in Figure 42. It should be noted that if the sealing arc is symmetric about the base line, that y=180o and RS(6)=180o. Neglecting the thickness of the vanes and assuming that the vanes are in continuous contact with the stator cylinder, the ideal volume of the expander' s cell as a function of angular displacement may be written as R ,(0) = Am. (0) AB (6 )] L (41) where Acy(6) and Acy(86) are the areas enclosed between the stator and rotor cylinders and the datum and the leading and trailing vanes respectively. The area functions have been calculated using the equations and numerical procedure presented in Badr et al. (1985). The actual volume of the expander' s cells differs by accounting for the volume of the extended portions of the leading and trailing vanes outside of the rotor' s slots. In order to calculate the kinematics of the vanes and the actual volume of the expander' s cell, the protrusions of the vanes from the rotor' s slots must be computed. The vanes are assumed to be rigid. R(6) is defined as the radius of the statorcylinder to the center of the rotor as a function of angular displacement. For a circular statorcylinder this quantity may be simplified and expressed as R (0)= ecos(y8)+ r +~e 2esrR ~yesi 7 (42) where Y'is defined as the angle between the arc' s center and that of the rotor. The vane' s protrusion from the slot may then be defined as X (0)= R (0 rR (43) The sliding velocity and the acceleration of the vanes may be determined by differentiating Equation (43) with respect to time once and twice, respectively. A FORTRAN subroutine has been developed to calculate the geometrical characteristics of a circular rotaryvane expander for a given set of input parameters. Thermodynamic Model To model the performance characteristics of an expander, the principles of conservation of mass and energy in each of the expander' s cells must be used. This will allow the prediction of the pressure, temperature and mass variations of the working fluid in the cells as a function of the rotor' s angular displacement. This will require accurate calculation of both the variation of the cell volume and the thermophysical properties from the geometric and thermophysical models, respectively. The basic geometrical relationships modeled then helped describe: * Variation of the cell volumes * Volume expansion ratio * Inlet and exhaust port area variations As mentioned earlier, in order to model the thermodynamic and throttling characteristics of an expander, the principles of conservation of mass and energy in each of the expander' s cells must be used. These would allow the prediction of the pressure, temperature and mass variations of the working fluid in the cells as a function of the rotor' s angular displacement. A computer program has been coded to calculate the mass, pressure and temperature variations in the expander' s charging, expansion, and exhaust stages. Figure 42 shows the various stages of flow of a working fluid through the rotaryvane expander. The following characteristics are calculated once the inlet state to the expander is defined and the mass, pressure and temperature variations in the expander are found: * Volumetric efficiency: an indicator of how well the expander' s cell was filled during the charging process * Throttling power factor: a ratio of the indicated power of the expander with only throttling losses in ports accounted for and the indicated power of an ideal expander * Throttling Efficiency: A ratio of the specific work of the expander with only throttling losses accounted for and the specific work of an ideal expander The throttling losses in the intake and exhaust ports are only presented here briefly but will be discussed and modeled in the subsequent chapter. Charging Process The charging process takes place at angular displacements of 0 <; B < 8,, + 3. The temperature of the fluid entering the expander can be determined from the degree of subcooling the fluid undergoes in the condenser. The saturation pressure corresponding to the saturation temperature of the condenser, the state of the fluid entering the expander can also be determined. This state is denoted by the sub script (int). The mass flowrate of the working fluid that fills the cavity, assuming steady flow and ignoring changes in potential energy, can be written as th,,, (0) = Cd Pmt Amt (B)YFmt (44) where the coefficient of discharge is assumed to be unity initially and will be determined by experimental data. The inlet throat area varies as a function of angular displacement and was found to obey the linear approximation that Wolgemuth and Olson (1971) have suggested. A typical linear approximation of the inlet throat variation is shown in Figure 43. The expression for the amount of mass contained in the expander cell at any angular displacement is the following m,(0) = m, (0)+i 0 (45) The first law of thermodynamics can be written for the process as follows (taking heat into the system and work done by the system as positive) = Q Wb + v inthin (46) dt m Assuming the changes in kinetic energy and potential energy are neglected, Ecy=dUy. The pressure within the control volume is also assumed to be uniform. Multiplying by dt and neglecting friction, internal leakage losses and heat transfer, Equation (46) becomes AU = r: (V2 V)+ mine hint (47) Solving for the internal energy of the refrigerant at the new time step, State 2, we find u2_ 11 2 ) mnhnt (48) m2 The density of the refrigerant at the new time step, State 2, is calculated as p2_2 (49) The charging process is assumed to be a constant pressure process (P1=P2=Pint). This conclusion is supported by much of the literature including Taniguchi et al. (1983) and Baek (2002). The mass in the control volume at State 2 is thus an unknown. In this case, the first law of thermodynamics can be written as AU = m2u 2 1~u 1 1p V2 V)+(m2 1, )hin (410) The mass at State 2 can be expressed however as na, = p,V, (411) Substituting Equation (411) into Equation (410) we get p,V,u, nzzu, = p, (y I )+(pzV, nzz )hmt (412) where p2 and u2 are the unknowns. Neglecting temperature gradients within the control volume, these two unknowns may be determined by iterating on the temperature of the control volume that corresponds to the known pressure, P2, and simultaneously satisfies the conservation of energy statement, Equation (412). The thermodynamic state of the control volume at the new time step or angular displacement has hence been fully defined and this procedure is carried out until the cutoff angle (8=8in+6). Expansion Process During the expansion process, 0,,, + 3<0 < ex, the mass in the control volume, mov, stays constant after the cutoff angle 8,a, = 8,m + 3 where 6in is the spread of the intake port and 8 is the angle between successive vanes (e.g. 6=45o for an eightvane expander). Assuming internal leakage losses are negligible, the mass in the control volume, mov, is assumed to be constant throughout the expansion process. If pressure gradients within the control volume, changes in kinetic and potential energy, friction and heat transfer are also neglected, the process between the current and new time step may be assumed to be isentropic and hence s, = s, (413) The density at the new time step may be determined from pt = (414) The thermodynamic properties at the new time step, namely temperature, pressure, and quality, can be calculated from Equations (413) and (414) with the use of REFPROP 7.0. This process is repeated until the end of the expansion process at a predetermined exhaust angle of 6ex. Exhaust process The exhaust process occurs at an exhaust angle 0ex < B < 8end 8out + 6, Where 8out is the spread of the exhaust port and 8 is the angle between consecutive vanes. During the exhaust process, the mass flowrate of the working fluid discharged from the control volume as a function of angular displacement can be determined from the following equation thes (8) = Cd,ex, (0) Acx (0)Ve (4 15) where pv is the density of the working fluid in the control volume at the current time step. The discharge coefficient, Cd,ex, iS an empirically determined constant that takes into account exit port losses. Here, the discharge coefficient is assumed to be unity. The variation of the exit throat area, Aex (6), can be seen to follow the linear approximation proposed by Wolgemuth and Olson (1971) in Figure 44. The amount of mass contained in the control volume at any angular displacement can then be expressed as where 0ex is the angle at the end of the expansion process. The first law of thermodynamics can be written for the process as follows dEc = Q Wbi yj2exhex (417) Neglecting changes in kinetic and potential energy leads to Ecy=Ucy. The exhaust process is assumed to occur at constant pressure P,, (Sx) = Ex and in an quasi equilibrium manner. Neglecting friction, internal leakage losses and heat transfer from the ambient, Equation (417) reduces to AU = Pex (V2 V) mexhex (418) Applying the same solution methodology as in the charging process, Equation (4 18) simplifies to p2u 2 1~u 1 Pex ( R) (P2L m 1)4 (419) where p2 and u2 are the unknowns. Neglecting temperature gradients within the control volume, these two unknowns may be determined by iterating on the temperature of the control volume that corresponds to the known pressure, P2, and simultaneously satisfies the conservation of energy statement, Equation (419). The thermodynamic state of the control volume at the new time step or angular displacement has hence been fully defined. Ideal Expander Evaluation For a given set of operating temperatures in a refrigeration system, the state of the refrigerant entering and leaving the expander may be determined. The resultant process volume ratio is defined as rv, =evapI1 (420) where v3 is the specific volume of the fluid at the condenser exit. The refrigerant may be a saturated or subcooled liquid at this state. This process volume ratio is expected to be smaller when the refrigerant leaving the condenser is subcooled. The builtin (or geometric) volume ratio of the expander may be expressed as rv,bln =(421) It should be noted that the terms builtin and geometric volume ratios are used interchangeably. If internal leakage losses are neglected, this parameter reduces to the ratio of the expander' s cell volumes since at both 6ex and 6in+a the mass in the cell volume is constant. If the builtin volume ratio is less than, identical to or greater than the process volume ratio then underexpansion, ideal expansion and over expansion will occur, respectively. The expander should not only match (or be fairly similar to) the process expansion ratio for typical system operating conditions but should also minimize the amount of wasted power recovery due to pressure losses incurred during under expansion. In the case of overexpansion, the higher pressure of the downstream reservoir may result in refrigerant flowing back into the expander via the exhaust port further complicating the actual exhaust process. Overexpansion is not accounted for in this study. Figure 45 illustrates the three possible scenarios depending on the builtin and process volume ratios. The appropriate selection of the dimensions of the expander is critical to ensuring adequate operation. In general, turbomachines are designed such that the volumetric flowrate of the working fluid is identical to the volumetric displacement of the device. For the case of an expansion device employed in a refrigeration system this equality may be expressed as 4 ~ = viz,mlv,, (422) where 0Z is the rotational speed of the expander in RPM and fi is the volumetric displacement per revolution of the expansion device. The righthand side of Equation (4 22) represents the volumetric flowrate of refrigerant in m3/S that enters the expander after leaving the condenser in either a saturated or subcooled liquid state. The rotational speed is the primary design variable for given operating conditions and geometry of the expander. As the rotational speed of the expander increases, frictional losses and internal leakage typically increase and decrease, respectively. An optimum operating condition exists where the product of the displacement volume of the expander in m3/rev and its rotational speed minimize friction, leakage losses and the manufacturing cost of the expander. In order to calculate the torque and power developed by the expander, the pressure forces acting on the vanes must be computed. If the pressure forces are assumed to act at the midway point of the vane's calculated protrusion from the rotor slots and no internal leakage losses are assumed past the vane tips, the following expression for the torque developed by one vane at any angular displacement may be written S(0) =X, (0) L P,(0) Pt,(6+ ) rR + (423) If frictional losses are also assumed negligible, the average of the sum of the torque developed by the expander at any angular displacement multiplied by the rotational speed is the power that may be extracted from the expander. The resultant power as a function of angular displacement may be expressed as The appropriate selection of the geometry and rotational speed of the expander ultimately depends on the application. Parameters of interest for typical operating conditions for a basic and modified refrigeration system are tabulated in Table 43. The apparent advantages of employing an expansion device include reduction in mass flowrate and process volume ratio, increase in the system COP, refrigerating efficiency and refrigerating effect. The network required by the system also decreases if the expander work is assumed to be ideally coupled to the compressor shaft. As the efficiency of the expansion device increases, it can be seen that further decreases in the mass flowrate and process volume ratio are obtained. Similar trends for various operating conditions, component efficiencies, degrees of superheating and subcooling are expected. In order to determine the work extraction potential of an expander with a known geometry, an alternative numerical solution procedure to that detailed in the charging, expansion and exhaust sections must be utilized. The charging and exhaust processes were assumed to be isobaric and hence the mass flowrate of refrigerant is unknown. There exists, however, a unique value of the incoming and leaving refrigerant mass flow rate at which the power extraction is optimum. The mass flowrate is hence iterated upon in order to satisfy Equations (412) and (419). Cerpnalkovski (1991) suggested typical values of aspect ratio (rR/L) of a rotary vane compressor of 0.50.8. For the purpose of this study the aspect ratio was assumed to be 0.46. The eccentricity of the rotor and stator cylinders was also assumed to be 2.6 mm. The dimensions of the expander are assumed to be 28 mm, 30.6 mm and 12.7 mm for the rotor radius, statorcylinder radius and the axial length of the expander respectively. The sealing arc is assumed to have an arclength of 6seai=40o. The most important geometrical design parameter, which ensures adequate size and performance of any expansion device, is the builtin volume ratio. Figure 46 shows the variation of the builtin volume ratio as a function of the intake angle for various numbers of vanes. The intake angle is found to be the most critical parameter that influences the performance of a rotaryvane type expander. For all intake angles analyzed, the thermodynamic performance and builtin volume ratio are maximum when the exhaust angle is 6ex=1890. The volume ratio is found to decrease as the intake angle increases independent of the expander' s number of vanes. As the number of vanes in the expander increases this decrease is found to increase dramatically. The increase in the number vanes may also be limited by the dynamics and mechanical strength of the rotor and the added frictional and internal leakage losses that may result. The expander's intake angle should hence be designed to optimize both the thermodynamic and geometrical performance. A single value of the intake angle may not optimize both simultaneously, however. Application dependent optimization is thus necessary. Although smaller intake angles result in larger builtin volume ratios, higher throttling losses are typically associated with them. The expander' s builtin volume ratio can be seen to decrease by 40%, 58.3% and 67% for the entire range of intake angles investigated for 4,8 and 12 vane expanders, respectively. Median values of the intake angle (6in=15o) and number of vanes (N=8) have been selected in order to avoid the aforementioned complications at which the volume ratio is ry,b=5.4305. The displacement volume of a circular rotaryvane expander may be computed for any given set of input parameters detailed in Table 43. The control volume analyzed is defined as the volume bounded by the statorcylinder, rotor, leading and trailing vanes and the two axial endplates. Figure 47 illustrates the ideal cell volume variation as a function of angular displacement for different numbers of vanes. The displacement volume per revolution is the cutoff volume multiplied by the number of vanes. Figure 4 8 shows the difference between the ideal and actual volume. By accounting for the thickness of the vanes, tv=4.2 mm, a slight shift in the volume curve is observed. This results in a deviation by as much as 89% and by as little as 1% at initial and at larger angular displacements. It can also be seen from Figure 48 that the maximum ideal and actual volume occurs at 6=184o and 6=180o respectively. The condensing and evaporating pressures corresponding to 50oC and OoC condensing and evaporating temperatures are 1.942 and 0.498 MPa, respectively. This corresponds to a process volume ratio of 14.74 if the refrigerant is assumed to be expanded isentropically. Figures 49 and 410 illustrate the variation of the pressure within the expander as a function of the volume within the expander for various intake angles and numbers of vanes, respectively. The pressure is found to be greater than the desired exhaust pressure primarily because the builtin volume ratio is not equivalent to the process volume ratio. From Figure 49, it can be shown that builtin volume ratios of 8.16, 6.6 and 5.43 corresponding to intake angles of So, 10o and 15o, respectively, correspond, to exhaust pressures 15%, 32.2% and 40% higher than the desired exhaust pressure. Figure 410, illustrates how the number of vanes affects the pressure variation in an expander for a given intake angle. It can be shown that builtin volume ratios of 4.083, 5.43 and 6.6 corresponding to 6, 8 and 10 vane expanders result in 53%, 40% and 26% higher exhaust pressures, respectively. These differences are primarily due to inadequate builtin volume ratios of the expander and result in less desirable thermodynamic performance. Unless a throttle valve or another means of expanding the discharging fluid to the evaporating pressure is used, flashing and/or other losses are imminent. For the purpose of this ideal analysis the losses due to underexpansion are not included in the models developed and it is assumed that a throttle valve further expands any underexpanded refrigerant to the evaporator pressure. Independent of the builtin volume ratio, the optimum performance of an expander is expected to occur when the mass flow of the working fluid is maximum. The maximum mass flowrate will likely have to be greater if the builtin volume ratio of the expander is inadequate. Accurate models for the mass flowrate of an actual expander may be developed in which inlet area, exhaust area, velocity and density variations as a function of angular displacement are modeled. Figure 411 shows the variation of the mass trapped in the expander' s control volume as a function of angular displacement for various intake angles. It can be seen that as the intake angle increases, the greater the amount of mass in the control volume during the expansion process. This results from the fact that the expander' s cutoff is delayed. These delays in cutoff are represented as lines (a), (b) and (c) respectively. It is found that the mass in the control volume during expansion is 50% and 28% higher for intake angles of 6=25o and 6=10o, respectively, when compared with that of 6= So Figures 412 and 413 show the variation of power extracted during the process expansion as a function of angular displacement for various intake angles and different numbers of vanes. Figure 412 shows that the maximum power extracted prior to the exhaust process is 1440 W, 742 W and 534 W for 6, 8 and 10 vane expanders, respectively. At the conclusion of the exhaust process, the net power output from the expander is 355 W, 305 W and 257 W corresponding to 6, 8 and 10 vane expanders respectively. It can also be seen from Figure 413 that as the intake angle increases the maximum power extracted prior to the exhaust process is 611 W, 690 W, 742 W and 794 W corresponding to intake angles of So, 100, 15o and 200, respectively. At the conclusion of the exhaust process, the net power output from the expander can be seen to be 309 W, 307 W, 305 W and 297 W corresponding to intake angles of So, 100, 15o and 200 respectively. Figure 414 shows the variation of the power extracted as a function of volume for a particular set of input parameters. The same general trends of Figures 412 and 413 is observed. Theoretical simulation models have been developed to analyze and evaluate the geometric and thermodynamic performance of a circular rotaryvane expander. The following conclusions can be made: * The builtin volume ratio can be seen to decrease by 40%, 58.3% and 67% for the entire range of intake angles investigated for 4,8 and 12 vane expanders respectively. The increase of the number vanes may be limited by the dynamics and mechanical strength of the rotor and the added friction and internal leakage that may result. Lower intake angles result in larger builtin volume ratios but higher throttling losses are typically associated with them. * As the spread of the intake angle decreases and the number of vanes increases, hence an increase in the builtin volume ratio, the resultant exhaust pressure is found to reach the evaporating pressure. These differences are primarily due to the inadequate builtin volume ratio of the expander and result in less desirable thermodynamic performance. * Unless a throttle valve or another means of expanding the exhaust fluid down to the evaporating pressure is used, flashing and/or other losses are imminent when the refrigerant is underexpanded. * As the number of vanes increases, the net power output of the expander decreases. For the cases investigated, as much as 75% of the power extracted prior to the exhaust process is consumed by the exhaust process. Compared to a 10vane expander the net work output of a 6vane expander is found to be greater by as much as 27% * As the intake angle increases, the maximum power extracted prior to the exhaust process increases. At the conclusion of the exhaust process, the net power output from the expander is found to deviate only 2% from the mean. The thermodynamic model developed in this section was ideal in its assumptions and analysis. It did not take into account losses that may arise due to throttling in the intake and exhaust ports, twophase internal leakage, friction, heat transfer, re compression or irreversible losses due to over or underexpansion caused by inadequate expander sizing. Chapter 5 details the theory and presents models of those aforementioned loss mechanisms. Once described, the models for these loss mechanisms will modify the thermodynamic model developed in this chapter to provide an accurate estimate of the expander' s detailed and overall performance. Figure 41. Flow diagram of the main computer program developed Table 41. Summary of rotaryvane literature Analysis No. Investigator Application 1 Peterson and McGahan (1972) Compressor 2 Badr et al. (1985a) Expander in ORC 3 Badr et al. (1985b3) Expander in ORC 4 Badr et al. (1985c) Expander in ORC 5 Badr et al. (1986a) Expander in ORC 6 Badr et al. (1986b3) Expander in ORC 7 Edwards and McDonald (1972) Expander in ROVAC S8 Robertson and Wolgemuth (1978) Expander in RC 9 Beck et al. (1966) Compressor in VC 10 Marsters and Ogbuefi (1972) Air Motor 11 Somayajulu (1971) Pump 12 BenBassat and Wolgemuth (1972) 2stage Exp in RC 13 Wolgemuth and Olson (1971) Expander in RC 14 Jacazio et al. (1979) Air Motor 15 Bransford and Stein (1960) Compressor in VC 16 Robertson and Wolgemuth (1975) Expander in RC 17 Barszcz, Z. (1980) Air Motor VC: Vapor Compression refrigeration system RC: Rankine Cycle ORC: Organic Rankine Cycle ROVAC: ROtary Vane Air refrigeration Cycle *Keenan and Keyes equation of state for steam Working Fluid Air General R113 R113 R113 R113 Air Steam R12 vapor Air Air Steam Steam Air Air and R12 Steam Air Eq of State Idealgas Idealgas Idealgas Idealgas Idealgas Idealgas Idealgas na Idealgas Idealgas K & K* K & K* Idealgas Idealgas Idealgas General xx x x x xX Base Line 6=0 to Charging Process 0<6<86+ Exhaust Process 8ex<6<2n: Expansion Process 86+8<6<6e Trailing vane Figure 42. Schematic of a generally oriented circular rotaryvane expander with 8 vanes described by two circular arcs Table 42. Geometrical input parameters Input Parameter Symbol Rotor radius, m rR Eccentricity, m e Angle between rotor and statorcylinder centers yr Stator cylinder radius, m rs= rR 8 Axial length of expander, m L=AR rR Number of vane s N Angle between successive vanes, deg 8=3600/N Thickness of vanes, m tv Inlet port arclength, deg 8in Exhaust port arclength, deg 6ex Arclength of sealing arc, deg 6seal 0.003 0.0025 ai 0.002 i 0.0015 0.001 0.0005 0 0 20 40 60 80 Angular Displacement, deg Figure 43. Variation of the inlet throat area with respect to angular displacement 0.003 0.0025 0.002 0.0015 0.001 0.0005 150 200 250 300 350 Angular Displacement, deg Figure 44. Variation of the exit throat area as a function of angular displacement for an 8vane circular MVE Ideal Expansion v, process = v,buitin Pint Under Expansion rv, process > v,buitin Over Expansion Tv, process < v,buitin Pex 6in 6in +6 6ex V Figure 45. Pressure variation as a function of volume in an ideal expander for the cases of ideal, over and under expansion. Table 43. Typical operating conditions for a basic and modified 2 ton system Expander mi Isenthalpic Isentropic Expansion nex,=0.45 nex,=0.85 Expansion ,g/s 49.6 48.61 47.77 47.5 va, m3Ikg 0.000924 0.000924 0.000924 0.000924 ry,p 16.3 15.6 14.97 14.74 COP 3.52 3.87 4.23 4.38 rlher, % 64.4 70.8 77.4 80.1 wexp, kJ/kg 2.89 5.46 6.42 wnet, kJ/kg 40.3 37.4 34.8 33.8 Qevap, kJ/kg 141.1 144.7 147.3 148.2 *R22, 2 ton cooling capacity, Tcond=50oC, Tevap OoC, 11,=0.85, no superheat, no subcooling, pressure losses in lines and components neglected 8 L 6 1~ 4 a N=6 .N=8 N= 10 N= 12 Intake Angle 8in, deg Figure 46. Variation of builtin volume ratio as a function of intake angle for different numbers of vanes 3.5E06 3.0E06 N=4 E 2.5E06 AR=0.46 e" FR=27.9 mm E2.0E06 N6e=2.7 mm 1.50 N=8 Si=150 > 1.0E06 'E N=12 5.0E07 0.0E+00 0 60 120 180 240 300 360 Angular Displacement 6, deg Figure 47. Variation of ideal volume as a function of angular displacement for different numbers of vanes 149 2.0E06 1.6E06 1.2E06 8.0E07 4.0E07 0.0E+00 AR=0.46 r,=27.9 mm e= 2.7 mml N=8 El.:., ,,= 1 8 9 0 100 200 300 400 Angular Displace me nt 6, deg Figure 48. Variation of ideal and actual volumes as a function of angular displacement 2500 AR=0.46 2000 Pinlet r,=27.9 mm ca ~ e=2.7 mm 150 Cn10 ,=1 50 N=8 60ut= 1890 t~1000 in= 5' 500 ~1)Losses Pexhaust 0.0E+00 5.0E07 1.0E06 1.5E06 2.0E06 Volum7e, m73 Figure 49. Variation of pressure as a function of volume for various intake angles 2500 e lniP 20 1E S1 00u AR=0.46 \ ~N= 6 4 rR=27.9 mm 500 N0 e=2.7 mm 6in= 150 )000 ''1w Bout= 1 8 9 j0 0.0E+00 5. 0E07 1.0E06 1.5E06 2. 0E06 2.5E06 Volume, m3 Figure 410. Variation of pressure as a function of volume for different numbers of vanes 4.0E04 Expansion AR=0.46 rR=27.9 mm e= 2.7 mm N= 8 R=58 rpm 60ut=1890 3.0E04 2.0E04 1.0E04 0.0E+00 (a() 100 200 300 Angular Displacement 6, deg Figure 411i. Variation of mass within the expander' s cell volume as a function of angular displacement for various intake angles AR=0.46 TR=27.9 mm e= 2.7 mm R=58 rpm em=150 60ut=1890 0.8 0.6 0.4 0.2 0 0 120 240 360 Angular Displacement 0,deg Figure 412. Variation of power as a function of angular displacement for different numbers of vanes 0. 8 8n20 ,=150 8,n=100O AR=0.46 ~ 06 rR=27.9 mm e=2.7 mm a N=8 S0.4 o a2=58 rpm 60ut= 1890 0 120 240 360 Angular Displacement 8, deg Figure 413. Variation of power as a function of angular displacement for various intake angles 0.6 ~haustAR=0.46 ExhaustR=27.9 mm 0. e=2.7 mm g~~ I. take and N= 8 a., Expansion s2=58 rpm 0.2 _Net Work o Output ~im 150 60ut=1890 0.0E+00 5.0E07 1.0E06 1.5E06 2.0E06 Volume, m3 Figure 414. Variation of power as a function of volume CHAPTER 5 PRIMARY AND SECONDARY LOSS MECHANISMS IN ROTARYVANE TWO PHASE REFRIGERATING EXPANDERS All turbomachinery operate with energy and mass losses. These losses may be attributed to twophase internal leakage, friction, throttling losses in the intake and exhaust ports, recompression in the expander cavity and over or underexpansion due to inadequate sizing of the geometric volume ratio. Primary Loss Mechanisms The aim of this chapter is to develop mathematical models that would account for the primary loss mechanisms of internal leakage and friction. The size of a rotaryvane expander is of primary interest due to the influence it has on the magnitude of loss mechanisms present. While rotaryvane compressors are typically very efficient, at smaller sizes, the effect of losses such as internal leakage becomes much larger. In rotary vane expanders of smaller sizes both the volumetric and adiabatic efficiencies are expected to be smaller. Depending on the operational and geometrical parameters of the expander, laminar and viscous twophase leakage flow within the expander may be present. Singlephase leakage models available in the literature must be revisited and modified accordingly. A dynamic frictional model for the expander must also be developed for ideal operation (i.e. no internal leakage) and modified to account for internal leakage accordingly. A comprehensive componentlevel model of inherent friction and internal leakage losses in a twophase circular rotaryvane expander used in a vapor compression refrigeration system is presented. The model establishes the efficiency and performance of the expander as a function of geometric and fluid parameters. Accurate modeling and prediction of frictional and internal leakage losses is vital to being able to accurately estimate the efficiency, rotational speed, and the torque and power produced by the expander. Internal Leakage Paths and Clearances The clearances between the rotor and stator cylinders, endplates and vanes provide the necessary seals of the expander cavity. Caution must be exercised when designing an expander' s assembly clearances. Depending on the operating conditions and geometric volume ratio, large temperature gradients may also lead to thermal deformations of these materials. The clearances must be minimized for each application to ensure control of internal leakage losses yet recompression of liquid may lead to inadequate operation or "liquid locking". The various leakage paths are tabulated in Table 51. The volumetric efficiency of an expander may be larger than unity due to significant increases in the consumption of the working fluid. This significant increase is primarily a result of internal leakage losses. The magnitude and sources of internal leakage must be identified and minimized. The magnitude and sources of internal leakage is significantly dependent upon the way by which the working fluid is introduced into the expander' s cavity. Figure 51 illustrates the difference between the conventional (a) and modified (b) methods through which the fluid is introduced into the expander's cavity. The "conventional" intake port is machined directly into the statorcylinder. The "modified" intake is comprised of slots machined in both endplates after which the fluid is introduced into the expander's cavity via a slot machined into the rotor at a specific angle from the slot. Upon the completion of the geometric, kinematic and thermodynamic models, the predicted pressure and quality of the refrigerant in the expander' s control volume are used to calculate the leakage of refrigerant through the various leakage flow paths. In order to model internal leakage between control volumes, the flow areas of the leakage paths, Aleak, must be estimated. The mass flowrate of internal leakage can be written in general form as rhleak (B) CPId (lea Aleak lea (8 UBI () (5 1) where Cd is an empirical discharge coefficient. The density and velocity of the leakage are a function of the angular displacement at which the leakage occurs and the thermodynamic state of the fluid. Of primary interest is the computation of the velocity. The net mass flow leaked into the cavity formed by the adj acent vanes, stator and rotor cylinders (see Figure 51) can be computed as libleak (8 jleak (B6 jleak (0) (52) Leakage from Path (6) is neglected. It should be noted that if the sealing arc is symmetric about the base line then gi=180o and RS(6)=rs. Types of TwoPhase Leakage Losses The maj ority of internal leakage models in turbomachinery presented in recent literature are developed for singlephase compressible flow. The friction associated with incompressible leakage losses through a duct or leakage path of constant crosssectional area affects only pressure in the direction of the flow. The velocity of the working fluid remains constant. According to Oothusizen (1997), in compressible flow, friction affects all of the flow variables, i.e., the changes in pressure cause changes in density which lead to changes in velocity For twophase flow this also necessitates vaporization of liquid, which alters the density of the working fluid significantly. Depending on the operational and geometrical parameters of the expander, turbulent twophase leakage flow within the expander may be present. In the case of twophase viscous leakage losses, the twophase mixture is assumed to be homogenous in nature. The idealizations adopted under this fairly common model include assuming that the vapor and liquid velocities are equal. The overall twophase flow is also assumed to behave like a single phase, uniformly mixed, having fluid properties whose values are, in some sense, mean values for the flow according to Carey (1992). According to Levy (1999), assuming homogenous flow also allows the ability to apply all available singlephase flow analyses and empirical correlations The density of the homogenous twophase mixture is computed as 1 x 1x =+ (53) P Pg fc The calculation of other necessary properties for the twophase mixture, such as the specific heats and viscosity, can be very troublesome. Many different formulations have been proposed throughout the literature. Among them, S= (1x) p, + x p, (54) 1 x 1 x = + (55) P P, Pf For example, a twophase mixture of water at P=500 kPa and x=0.2 yields a viscosity of 146.09, 53.52 and 15.968 CIPa s from Equations (54), (55) and (56), respectively. According to Carey (1992), Equation (55) is the most common. Properties can also be computed by utilizing the concept of the homogenous void fraction ot, Pfx a = (57) p, x + (1 x) p, and hence the dynamic viscosity can be computed from pu= pf (1 a) + pUgC. This method will be used since the computed value is identical to that obtained from Equation (56). In the same manner the specific heats and thermal conductivity can be computed. Viscous effects must be accounted for when computing the pressure drop and mass flowrate through radial clearances, e.g. flow through minimum clearance. These channels are typically long and wide when compared to the height of the channel. Viscous effects may be neglected when dealing with nozzles or short ducts. The axial leakage flow between the vanes and the endplates is an example where viscous effects may be neglected. The flow of the twophase compressible leakage, accounting for friction, can be modeled as adiabatic Fannoflow. Figure 52 shows a schematic of a typical leakage path. The dimensions of the leakage path, crosssectional area and length, are known and depend on the leakage path under consideration. The exit, (e), could be choked depending on the difference between the pressure of the reservoir and back pressure at local angles 6 and 6+6, respectively. Darby (2001) concludes that the ratio of the sonic velocity in a homogenous mixture to that in a gas alone is much smaller than unity. In this case choking can occur in a two phase mixture at a significantly higher downstream pressure. This corresponds to both a lower pressure drop and mass flux. The flow is choked when the velocity at the exit plane is equal to the speed of sound. For a nonflashing liquid and an ideal gas mixture, the maximum mass flowrate in the channel can be computed. The isentropic speed of sound for a homogenous two phase mixture can be computed as a =a (58) The governing equations and the discretized form of those equations are presented in Table 52 and are derived from first principles and describe adiabatic Fanno flow from a reservoir. It should be noted that the volume of the leakage channel is V=Hwl and the mass flowrate through the channel is in = p,u,Hw The Darcy friction factor,J; is assumed constant over the length of the leakage channel. This is a fairly reasonable assumption since the flow is typically found to be fully developed over a majority of the channel length. For Reynolds numbers in the lower range of the turbulent region, the modified Blasius correlation is f~ = 0.33 Re0.25 (59) where the Reynolds number is defined as ReH eH/ve This correlation has been shown to be in good agreement with various experiments throughout the literature. The momentum equation can therefore be expressed by I1.75 (i: 4) 0.165 e 1.25 e"u (510) The methodology used to solve for adiabatic Fannoflow through a leakage path is an iterative procedure. The state of inlet to the channel is known. Depending on the leakage path and the state of the refrigerant, the flow may be of an incompressible liquid or a compressible twophase refrigerant. The unknowns, in Equation (510), that remain are ue, thz, Pe and pe. The iterative procedure calls for an initial guess at the exit plane of the channel where the flow is assumed to be choked. An initial guess of the pressure at the exit plane may correspond to the average pressure that exists in the adj acent expander cell. The flow is assumed to be isenthalpic or isochoric in the case of twophase or liquid flow, respectively. In the case of the twophase flow the quality is known. Based on the initial guesses, the speed of sound can be calculated. If the flow is choked at the exit plane, i.e ue=a, then P is iterated upon until Equations (55), (58) and (510) are satisfied simultaneously. If the flow is viscous and the exit plane is unchoked, the average velocity of the leakage can be determined by solving generalized Couette flow, see Figure 53, the flow is driven by both the shear of a moving wall and a given pressure differential. Solving the momentum equation and applying the noslip and moving wall boundary conditions the velocity distribution is 1 dP c r u(y> (y2 SP) (511) pu dxe S The mean velocity between the plates is defined as u,, u(y)dy (512) r=0 and after integration is found to be cor 82 dP u = (513) "' 2 12, d If the flow in the leakage path can be modeled as isentropic flow through a nozzle whose throat is choked then the initial guess used to evaluate the sonic velocity is P,' = E: and se = s,. The density is then calculated. The pressure and density at isentropic conditions, at the exit plane, are iterated upon accordingly until the computed speed of sound is identical to the relationship obtained from the energy equation, ue~ = J2(h he). In the case that the isentropic flow is unchoked, the exit plane pressure is equal to the back pressure, Pe=Pb and se= sl. The thermodynamic state at the exit plane can then be established and the velocity at the exit can be determined by Equation (58). Axial Clearance Between Rotor and End Plates The flow of the fluid between the rotor and endplates can be modeled as that of a fluid flowing in a narrow gap between a disc which rotates within a chamber of finite dimensions. The boundary conditions imposed on the periphery of the rotating disk are nonaxisymmetric in nature due to the pressure distribution of the fluid in the expander' s cavity. The effects of the vanes and their slots are neglected. The characteristics of the flow as well as the complexity of the solution can vary significantly depending on the order of magnitude of several key dimensionless variables. The dimensionless governing equations yields key dimensionless groups that govern the flow and are found to be the local rotational (disk) Reynolds number in terms of Si, the Euler number and the gap aspect ratio, S. If the rotational speed of the rotor is to in rad/s then these parameters are defined as S =R (514) Eu=2 (515) Re, = m (516) where AP in the Euler number corresponds to the maximum pressure differential on the rotor' s outer boundary, i.e. the intake and exhaust conditions. It should also be noted that in rotating disk problems the rotational Reynolds number is utilized instead of the radial Reynolds number which is defined as Re = corR61/,l, For the same flow conditions, the use of the latter is typically three orders of magnitude larger. Daily and Nece (1960) have identified four different modes of flow for given geometrical and flow characteristics. Of interest in this study are the laminar and turbulent cases corresponding to a close gap where boundary layers on the rotor and end plate are merged. In this case a continuous variation of the velocity across the axial gap exists. The rotational Reynolds number must be small in the gap, Re~ <1, for this type of flow to exist. Separate boundary layers exist when the axial gap exceeds the total thickness of the two boundary layers. The condition for laminar flow can therefore be estimated from Daily and Nece (1960) as Re4 S2 < 105 The Euler number which is defined as the ratio of the maximum pressure differential to the centrifugal pressure produced during rotation is assumed large, i.e. Eu Re~ >1. The gap aspect ratio must also be substantially larger than unity. If these four conditions can be satisfied simultaneously then a zerothorder solution approximates the solution to the NavierStokes equations. This solution consists of a power series of Real, e.g. ur = ur, + Re~ uz + Re~ u, +..., expanded around the asymptotic solution of Real approaching zero. Bein et al. (1976) concluded that this is a reasonable assumption for Eu 2 0 . It must be determined whether the following analysis is valid for the flow of two phase fluid in the axial gap. Due to the vaporization of liquid in the expander' s cavity, the thermodynamic properties vary significantly. Coupled with the significant variation of intake and exhaust parameters, geometry of the leakage gap and rotational speed of the expander, the aforementioned constraints may not be satisfied. In order to determine the operational conditions under which the analysis is valid the following operational parameters considered are presented in Table 53. It can be shown that the flow is laminar for all parameters investigated at lower rotational speeds, i.e. O2<500 RPM. Depending on the geometric size of the expander, the expander' s actual rotational speed realistically doesn't exceed this value. Based on the analysis of these operational conditions, an order of magnitude analysis of the flow dimensionless parameters is presented in Table 53. It maybe concluded that the zerothorder solution is appropriate. The location of the phase interface in rotating, eccentric complex geometries is very difficult to predict. If sufficient centrifugal forces are produced due to high rotational speeds it may be assumed that the maj ority of the leakageflow in the axial gap is vapor. This arises due to the tendency of the dense liquid to flow in the vicinity of the statorcylinder wall due to significant centrifugal forces. Hence the incompressible form of the general equations with constant properties, evaluated at some mean value, is used. Neglecting body forces, terms of order 1/S2 and equating terms with Real, the zeroth order dimensionless 3D NavierStokes equations in cylindrical coordinates are solved in order to determine the velocity and pressure field within the narrow gap. If a gap width 81 exists between the rotor and the end plates, then the dimensionless governing equations can be reduced and written as follows 18(ruo+ 180+ = 0 (517) "2 = Eu Re~ (518) 82 0 0= Eu Re~ (519) Co = 0 (520) where the dimensionless variables are defined in the nomenclature. According to Equation (520), Po = P0 (r,0) The boundary conditions can be written as follows, Fo (T, 8, z = 0) = 0 70 (T, 8, z = 0) = 0 wo(F,0,z=0)= 0 (521) uo (F, 8, = 1)= 0 wo(r, 6,7=1)= 0 (522) Po (r = 1, 8) = PN (0) where Pcy(6) is a linear piecewise function that closely approximates the actual pressure distribution around the rotors outer boundary and is presented in Figure 54. A linear approximation first presented by Bein et al. (1976) and furthered by Badr (1985) for a typical pressure profile is compared to numerically integrated Fourier constants in Equation (525). It can be shown that 100 terms in the summation of the Fourier constants yield the actual pressure distribution. Depending on the geometric volume ratio of the expander, the difference between the linear approximation and can vary significantly. An expander with a volume ratio of rv=3.916 is analyzed in Figure 54 and a maximum difference of 40% is found to exist between. This greatly influences the accuracy of the computed radial velocity. The zerothorder solution of the following simplified set of equations and satisfying all necessary boundary conditions yields Bein et al. (1976) as such Eu Re4 dp IT = _ Z) (524) S2 dr Eu Re4 1 87, 2 r 80 Substituting Equations (524) and (525) into the continuity equation, Equation (517), and applying the boundary conditions in the axial direction yields V P, = 0 (526) Solving Equation (526) by means of separation of variables, the general solution for the pressure distribution in the gap is Polf,8) = ao + blnr + a [(".' + b,, ) cos n9i r + c i"+d,,r") sin n0s (527) The Fourier constants can be determined from the specification of the pressure distribution on the outer boundary of the rotor (see discussion of Figure 54). The radial velocity distribution can be found by differentiating Equation (527) with respect to the radial direction and substituting that result into Equation (523). The total dimensional leakage mass flowrate in the radial direction with respect to the rotor is tleak,1 (0) = 2PN.(0) 4,(r = 1, 8) wr 3,(528 The value of the mass flowrate is negative if the flow leaves the expander cell. This model doesn't take into account choking, which is likely, since the velocity distribution at the rotor' s outer boundary is of primary interest. Leakage around tips of vanes Depending upon on the method by which the high pressure refrigerant is introduced into the expander' s cavity; see Figure 51, leakage due to insufficient undervane fluid pressure or inadequate force/absence of mechanical springs may lead to significant leakage losses several orders of magnitude larger than other leakage paths. Continuous and sufficient contact between the vanes and the statorcylinder is necessary to subdue or minimize this type of leakage. The maj ority of leakage of this type may occur during the intake process where low rotational speeds cause inadequate centrifugal forces to keep the vanes in contact with the statorcylinder. The existence of both low rotational speeds and inadequate undervane pressure can be predicted by the frictional model developed. The frictional model is presented later in this chapter. It should be noted that the reaction force, Fn(6) (see Figure 55), is predicted by the friction model and accounts for, among other things, the sliding velocity and acceleration of the protruding vanes as well as the undervane pressure. If the vane has lost contact with the statorcylinder, the value of this normal force is negative, and the leakage flow area would be computed as 4ak, (0) = 8, (0)L = X(0)L (529) where X(6) is the instantaneous protrusion of the vane from the rotor slot at the angular rotation of the rotor where the loss of contact has occurred. When the vanes establish contact with the cylinder it is assumed that the leakage area is negligible and that this occurs until the start of the sealing arc. There may exist leakage around the tips of the vanes during the spread of the sealing arc due to a clearance gap 83 between the statorcylinder and rotor that may be due to an assembly clearance or due to machining limitations. This radial leakage is treated in the next section. Due to the short nature of this leakage path, t,, the leakage of the twophase fluid in this path is assumed to be that of fluid in a convergentdivergent nozzle, i.e. isentropic flow. It should be noted that if the incoming fluid is introduced into the rotor' s slots than the internal leakage associated with weak undervane pressure can be neglected. For this design, internal leakage around the tips of the vanes can be neglected. The highpressure incoming refrigerant is first used to provide sufficient undervane pressure so that continuous contact between the vane and statorcylinder may be achieved. Leakage past the sides of the vanes In general, the axial width of this leakage path may be estimated by accounting for the thermal expansion of the vanes in addition to the gap that exists due to the thickness of gaskets, 6, and other assembly clearances. The operational length of the vane can be computed from the known material's coefficient of linear thermal expansion, Ly L,,o = aYLY,,oT, and the temperature difference that the vane encounters relative to ambient conditions. The mean temperature of the vane is computed as the average temperature of two adj acent cells. It can be shown that even at the moderate temperature differences realized within an expander's cavity this effect accounts for a 0.3% change in the length of the vane and is therefore neglected. The axial width of the leakage path is assumed constant and equivalent to the gasket thickness s33) 6g (530) The height of this leakage channel is estimated by subtracting the height of the gap realized due to leakage around the vane tips, if any, upon loss of contact with the stator cylinder, 62(6). The total leakage flow area is then calculated as Aleak (0) = 2 X (0) 6, (0)] S (0) (53 1) Due to the short nature of this leakage path, ty, the leakage of the twophase fluid in this path is assumed to be that of fluid in a convergentdivergent nozzle, i.e. isentropic flow. Leakage between the faces of the vanes and the side walls of the rotor's slots The leakage from this path is typically neglected due to the existence of two contact lines across the axial length of the rotor slots. These contact lines result from the reaction forces FL(6) and FR(8) (See Figure 55). Negative reaction forces predicted by the friction model represent a loss of contact between the vane and the rotor slot. The control volume to which the mass and energy are added or subtracted depends on which vane face the loss of contact occurs. If the fluid intake is through the rotor slot the leakage through this path may be significant and comparable to other paths. Viscous effects need to be considered since the leakage flow path is wide and long, Hy. The leakage flow area is computed as Aleak 8 (t, t,)L (532) The Leakage from the expander to the cavity beneath the vane may also be comparable if tsty is large. Leakage in radial gap between the rotor and stator cylinder As the pressure differential between the intake and exhaust ports increases and the number of vanes decreases, this leakage is typically the largest contributor to internal leakage. This leakage flow path arises if the angle between successive vanes is larger than the spread of the sealing arc (spread of minimal clearance) between the rotor and stator cylinder i.e. 8, > 6 If this is the case, the expander cell is in simultaneous contact with the intake and exhaust ports. This overlap causes leakage flow from the inlet to the exhaust ports against the direction of rotation. The severity of this leakage path is a function of the number of vanes and the mean radial gap height 84 that exists between the rotor and statorcylinder due to assembly operations or machining limitations. This leakage flow path would occur for the leading vane's angular displacement of 0 < 0 < 8 8,,, The flow in this leakage path is modeled as adiabatic, onedimensional Fannoflow. It should be noted that leakage through this path can only be neglected if sufficient centrifugal forces or undervane pressure exists to maintain continuous contact of the vane with the statorcylinder. Typically an insufficient undervane force exists due to the absence of highpressure fluid (or presence of lowpressure residual fluid) due to the theoretical completion of the exhaust process. The magnitude of the normal force Fn(6) determined by the frictional model aids in this prediction. The flow in this leakage path would necessarily be choked for large geometric volume ratios or uncontrolled expansion in the exhaust port if no throttle valve is downstream of the expander. Friction Model Prediction of the power output and developed torque of the rotaryvane expander requires accurate modeling of frictional losses incurred in the expander. The primary frictional losses in the rotaryvane expander result from: * Rubbing of the vanes against the statorcylinder * Rubbing of the vanes against the walls of their rotor' s slots *The resultant viscous drag acting on both sides of the rotor from the leakage flows through the axial gaps between the rotor and the endplates. A steadystate mathematical model that predicts frictional losses within a rotary vane expander must be coupled with geometric, thermodynamic and to leakage models in order to provide for a better estimate of the mechanical efficiency and actual power produced by the expander. A general dynamic model that incorporates the main sources of friction within the rotaryvane expander is presented in this section. Effects of pressure forces, reaction forces, sliding friction, viscous drag, gravity and inertial forces must all be accounted to understand the relevance and magnitude of these effects. Figure 55 is a schematic of a free body diagram of a vane protruding out a rotor slot at a local angle 6. In order to model frictional losses in a rotaryvane expander, vane forces resulting from pressure loading, vane inertia and body forces due to radial and Coriolis accelerations must be determined. Sliding friction must also be considered between the vanes and the rotor slots and statorcylinder. These forces and frictional losses continuously change, in both magnitude and direction throughout the expander due to continuous changes in complex geometry. The dynamic model developed assumes that the vanes are rigid and that the coeffieient of friction is constant. The conditions for dynamic equilibrium are solved simultaneously to determine the unknown reaction forces based on a freebody diagram of a single vane. Upon determining the reaction forces, the power required to overcome the resisting frictional forces can be computed. Below is a detailed description of the various forces as well as simplifying assumptions that have been made. A pressure force on the base of the vanes is assumed to act at midthickness of the vane as a result of incoming fluid pressure or a spring force utilized to maintain vanetip and statorcylinder contact. This pressure force at the vane base can be expressed as follows Fb = hPinistt,L (533) where h is a proportionality constant that can be evaluated from calculating throttling losses to or from the cavity beneath the vane. If the fluid is introduced directly into the rotor slots for the spread of the intake port, 6in, and assuming no throttling losses then h=1. If the fluid is introduced into the expander' s cavity directly then throttled leakage flow will provide the pressure force on the vane base (e.g. h=0.75). If correctly sized and assembled springs or a means for adequate pressurization of the slots are used then h=1. The pressure forces exerted on the vanes from either side FPR and FPL can be expressed as FPL8) Piv (6) X (6)L and FPR8 P ov (6 + 6) X (6)L respectively. If leakage losses through the vane rotorslot gaps are neglected then these pressure forces are assumed to act midway between the rotor' s outer boundary and statorcylinder' s wall. If a gap exists between the vanes and the rotor slots, the orientation of the pressure loaded vane, see exaggerated effect in Figure 55, provides two sealing surfaces. The portion of the vane that protrudes from the slot is denoted by X(6). The reaction forces FL(6) and FR(8) are aSSumed to act at the points of contact of the vane and the rotor slots on the left and right faces of the slot, respectively. These forces are actually distributed along a finite distance along the side of the vane and not at a point depending on the vanetoslot clearance. Since the vanes are assumed to be rigid, the friction forces are assumed to act along the surfaces as CL,FL (8) and CpFR e) respectively. The sub script r denotes the rotor material. The reaction forces Fn(6) and Ft(6) result from the vanetip and statorcylinder contact where F (8) = C1sFt (e) The vanes are assumed to be in continuous contact with the statorcylinder. The sub script s denotes the statorcylinder material. The assumption that the friction force (e.g. CL,FL ) is proportional to the normal contact force (e.g. FL) may not accurate since large local velocity gradients at the interface may severally alter the frictional losses. This may also be the case at the vanetip and statorcylinder interface. It should be noted that Figure 55 is valid for a vane that has no vanetip curvature. If the vanetip is round or altered in any way there will exist symmetric radial forces on either side of the normal force equal to the pressure on that side of the vane multiplied by the proj ected area of that surface. The sliding and centrifugal accelerations of the moving vane from the rotor slot result in a radial body force Fa(6) which can be expressed as F, (6) =m m/Acc(6) +r,,,(6) to (534) where rm(6) denotes the distance from the center of the rotor to the center of mass of the vane. The mean tangential body force Fe(6) that arises due to Coriolis acceleration of the vane can be expressed as Fo (6) = 214 Vel(6) co (535) where Vel(6) and Acc(6) represent the sliding velocity and acceleration of the vane respectively. The mass of the vane is assumed to act at the geometric center of the vane (i.e. Hy/2 and t,/2). From the following freebody diagram, Figure 55, the three conditions of dynamic equilibrium can be written as follows Fb 1rFL (8) rLFR (6) m,,gcos6+ Fa (6) F (6) =0 (536) FL (6) + mvg sin 6 Fe (6) FR (6) + FPL(8 FPR(8 sLFn (6) = 0 (537) mvg sin 6 Fe (6) FR()H,X(6 PL FR 6 22 2 (53 8) where Equations (536) and (537) represent the net summation of forces in the radial and tangential directions equal to zero respectively. Equation (53 8) represents the net summation of moments about point O equal to zero wherein the direction of rotation of the expander is assumed positive. It should be noted that the direction of some of the forces change depending on whether the vanes are protruding out during the intake and expansion processes or forced back into the vane slots during the exhaust process. The three equations can be simplified, rearranged and written in matrix form as aX = b (539) where matrix a represents the coefficients of the unknown reaction forces of matrix X= FR (eF 8 L() and matrix b contains known parameters such as pressure and body forces. Once this matrix is solved at each angular displacement 6 of the leading vane the reaction forces can be determined. The reaction forces in matrix X reveal the movement of the vane in the rotor' s slot and can predict the loss of contact with the statorcylinder or faces of the rotor slots. It should be noted that the coefficients in matrix a should be modified according to the vane's inward or outward movement relative to the slot. The mechanical efficiency and power losses of the expander due to friction can then be predicted. The frictional torque per angular displacement 6 due to vanetip (first term) and net vaneslot friction (second term) can be computed from Tse (8) = MsF, (6)[rR + X(6)]+ CtlFL (6)c + FR ()]Vel(6) (540) The total frictional loss, Tst~, in the expander is computed by summing Equation (5 40) through a complete revolution of the rotor. The contribution of each vane is accounted for and its contribution to the total torque is then averaged to yield Tstm,. No rubbing frictional forces exist between the sides of the vanes and the end plates due to the axial gaps between the rotor and the endplates. The leakage through those gaps, as determined previously, will lead to viscous drag. In order to model the viscous drag due to the axial leakage between the rotor and endplates the viscosity of the twophase fluid must be predicted accurately. The pressure distribution in the axial gap P(r,6) was derived previously. The pressure is assumed to be invariant in the axial direction. The state of the twophase liquid can be determined by assuming isenthalpic expansion in the radial and azimuthal directions. The flow in the axial gap is driven by both shear caused by the rotation of the disk and a pressure differential between the intake and exhaust ports. This results in a combined Couette Pouisselle (generalized Couette) flow, see Figure 56, in which the radial velocity can be expressed as 1 dP c u(Z) = (z2 3,z)+~z (541) p,,, dr 6, The total torque produced by viscous drag on both sides of the rotor is expressed by which can be integrated numerically. The total power loss is then calculated by PRoss = (Ts,m, + Tyd)bZ (543) where 0Z is the angular speed of the expander in RPM. Uncertainties regarding the gap size are a significant obstacle to quantifying the magnitude of leakage losses through certain leakage paths. These uncertainties are presented later. The base case simulations detailed below are valid for an eight vane circular expander of general orientation (i.e. yi=161.5 and RS(0) + rs) with a geometric volume ratio of rv=3.26 corresponding to 6in=3 5o and 6ex=189o whose physical dimensions mimic a modified GAST NL32NCC1 airmotor. The rotational speed of the expander is O2=300 RPM. The inlet conditions to the expander correspond to a saturated liquid at a condensing temperature of T=45oC. As previously mentioned, the estimated frictional forces within the expander are used to predict the movement of the vanes within their rotor slots. The profile of the vanetip is of significant importance in determining the forces acting on the vanetip. Figure 57 shows the instantaneous variation of reaction forces on a single vane with no vanetip curvature during one revolution of the rotor. It is assumed that a circular pressurizing grove ensures that h=1 through out one revolution. It can be seen that the normal force tends to the same variation as the pressure inside the expander' s cavity due to the significant contribution of the undervane pressure and absence of resisting forces in the opposite direction. It should be noted that no loss of contact is predicted for any of the reaction forces. It can be shown that for vanes with no vanetip curvature an insignificant undervane pressure (h=0.1) is necessary to maintain contact with the stator cylinder. Figure 58 is similar in nature to Figure 57 but for a vane that has curvature at the vanetip (i.e. addition of symmetric radial forces about normal force). It can be seen that the normal reaction force is negative, denoting a loss of contact, during 6in+6<6 corresponding to a maj ority of the expansion process. The increased pressure gradient across the vane in this case may lead to excessive leakage losses. This information is passed to the appropriate internal leakage code. The use of materials such as graphite, erode and match the profile of the statorcylinder depending on the intensity of the under vane pressure. The density of the material should be large enough to provide sufficient centrifugal forces if and when inadequate undervane pressures exist. Simulations were run to find the minimum value of h in order to obtain a positive reaction force at the vanetip statorcylinder interface denoting contact with the stator cylinder. Values of h=0.75, 0.85 and 0.95 were simulated. It was found that due to the curvature of the vanetip, only a value of h>0.95 would suffice. Figures 59 through 512 show the variation of leakage to and from the expander cavity by different leakage paths through one revolution of the rotor. Figure 59 shows the variation of nonaxisymmetric leakage from the expander cavity as a function of angular displacement for different intake angles. It is ensured that the governing dimensionless variables satisfy the constraints and assumptions that govern the flow. The use of choked flow relations for this leakage path does not grasp the underlying physics; magnitude and direction, associated with the flow between a rotating and stationary disk with nonaxisymmetric boundary conditions. It can be shown that if choked flow conditions are assumed at the rotor boundary then the leakage from, model cannot predict otherwise, the expander cavity is over predicted throughout the maj ority of the intake and exhaust processes. The current analysis overpredicts the cell leakage when compared to the choked flow model during the expansion process solely due to the accuracy of the pressure profile used to approximate the nonaxisymmetric boundary condition. Figure 510 illustrates the variation of the nonaxisymmetric leakage as a function of angular displacement for both the ideal and throttling cases. As the inlet angle decreases the potential for leakage increases significantly during the charging and expansion processes. For all leakage paths considered, the velocity of the leakage flow is calculated initially using the general Couette flow velocity profile determined above. If the flow is twophase, the speed of sound is calculated to provide a reference. If the computed velocity using the general Couette flow model exceeds the speed of sound, then the model switches over to a choked flow regime corresponding to a maximum leakage flow rate. These general trends are apparent from Figure 511. Figure 511 illustrates the total variation of flow to/from the expander cavity by means of leakage past the sides of the vanes. Contact between the vanetip and stator cylinder is assumed. A constant gap size is assumed. In actual operation, upon loss of contact, the vanes do not necessarily retract all the way back into the rotor slot leaving the leakage channel height X(6) as assumed in the above derivation. The leakage mass flowrate during the constant pressure intake and exhaust processes can be seen to increase and decrease, respectively with the oscillating variation of vane protrusion X(6). This effect is more evident in expanders with a larger geometric volume ratio. The leakage mass flowrate through the minimal gap that exists between the rotor and the statorcylinder is significant but constant for the duration 0<6<66seal, where 6seat is 400. The contribution of this leakage path to the total leakage flowrate increases with the decrease of the number of vanes. The start of the intake port may be delayed, if necessary, to minimize leakage from this path. The magnitude and direction of the leakage between the sides of the vanes and the rotor slots depends on the method by which the fluid is introduced into the expander's cavity. Figure 512 shows the variation of leakage into the expander cavity as a function of angular displacement. This leakage path only exists for the duration of the intake port. There may be leakage from the expander cavity via this leakage path during the remainder of one revolution. If the flow is introduced through the rotor slots, the velocity of this leakage path, assuming no throttling, would be that of an incompressible liquid in shear driven Couette flow. Here the plate moves with a velocity corresponding to the instantaneous sliding velocity of the vane. The leakage mass flowrate can be seen to increase proportional to the outward sliding velocity of the protruding vane. Of primary significance for an adequately designed expansion device is the ratio of total mass flowrate accounting for leakage and the corresponding ideal case, i.e. a leakage ratio me, at The mass flowrate through the expander accounting for leakage madeal maZctual = N, mov (B + 6) (544)l where the first term in the bracket represents the ideal mass flowrate and index i represents the leakage path. For the base case simulations the leakage ratio is r=10.9. This is significantly large and due to the low rotational speed of 300 RPM. Figure 513 shows the variation of the ideal and actual mass flowrates as a function of rotational speed. It can be seen that the leakage mass flowrate decreases significantly as the rotational speed of the expander is increased. The ideal mass flowrate increases in a steady manner. The operational rotational speed of the expander is a design choice that may be optimized by the proper selection of volumetric displacement for the inlet flow conditions. The leakage ratio is r=30.6 and 4 at rotational speeds of 100 and 1000, respectively. The actual mass flowrate curve increases linearly because all of the internal leakage paths, with the exception of axial flow between the rotor and endplates, is assumed to be independent of speed. Figure 514 illustrates the variation of the ideal and actual mass flowrates as a function of the number of vanes for an expander operational speed of 500 RPM. The ideal mass flowrate decreases since the volume of the cavity and the amount of mass in the expander cavity at the cutoff angle decreases significantly. The amount of leakage is seen to increase due to a larger contribution from the leakage mass flowrate through the radial gap, minimum clearance, between the rotor and statorcylinder. Caution must be exercised when increasing the number of vanes due to possible increases in friction and decrease of mechanical strength of the rotor. A thermodynamic and fluid dynamic model of the primary loss mechanisms in a circular rotaryvane expander has been developed as a function of design and fluid parameters. The following conclusions can be made: * The curvature of the vanetip can severally impact the amount of leakage past the vanetips due to loss of contact with the statorcylinder. Even if no throttling is assumed in the intake port, there is a loss of contact with the statorcylinder through out the duration of the expansion process. * Vanes should be made out of highdensity materials that can erode and mold to the statorcylinder geometric curvature. This would eliminate the need for adequate undervane forces through intake ports or cumbersome, unreliable springs. * Leakage losses from a maj ority of leakage paths cannot be necessarily neglected in twophase rotaryvane expanders. Unlike singlephase rotaryvane turbomachinery, significant variation in density and speed of sound with the vaporization of liquid significantly alters the leakage flowrates. * The leakage losses from the nonaxisymmetric flow in the axial gap between the rotor and endplates is significant. The model developed is relatively ideal in its assumptions and doesn't take into account separated boundary layers, choking or turbulent fluid flow. A computational model must solve the compressible Navier Stokes equations in order to do so. * Increase in rotational speed decreases internal leakage losses significantly. Further work must be made to determine the magnitude of detrimental effects such as friction and viscous drag. * A decrease in the number of vanes increases the contribution of leakage through the minimal radial gap between the rotor and stator cylinder. * Sizing of the rotaryvane expander for twophase applications is critical with regard to determining the optimum operational speed to reduce the loss mechanisms presented in this study. * Uncertainties regarding the gap size are a significant obstacle to quantifying the magnitude of leakage losses through all the leakage paths during operation. TwoPhase Throttling Losses in the Inlet and Exhaust Ports The state of refrigerant that enters the expansion device is of great importance. Unlike the conventional throttling valve, the state of the refrigerant may vary significantly from condenser exit conditions to the expander cavity. This may be due to significant throttling losses within the inlet port and internal contractions, enlargements and bends within the expansion device. This may also be partly due to the fact that the distance downstream over which the influence of the feature is felt is greatly increased in twophase flow. A model for the prediction of the pressure losses of twophase flow due to these flow restrictions is presented. An algorithm is presented and developed by which the actual state and amount of refrigerant entering the expansion device can be computed. Figure 515 illustrates the difference between the conventional and modified methods of intake. The refrigerant leaving the condenser may be either saturated or subcooled liquid. Depending on the degree of subcooling, pressure drops resulting from throttling in the expander' s intake port and friction due to flow restrictions may cause the refrigerant to drop into the twophase region. These pressure losses should be minimized in order to maximize the pressure differential utilized to produce work in the expander. In the case of underexpansion, where the geometric volume ratio is not sufficient when compared to the process volume ratio, pressure losses realized in the intake and exhaust ports are a necessary loss mechanism after which no further throttling may be needed. The analysis of throttling in the ports can be divided into two distinct analyses. The difference in analysis depends solely on the method the refrigerant enters the expander cavity. The equations for the static pressure drops, frictional pressure losses and contraction coefficients for various geometries are presented below. Calculating throttling losses and the actual mass flowrate is presented later. This will aid in the evaluation of how well modeling the intake and exhaust processes as isobaric is. During the intake process the refrigerant goes through numerous pressure drops as a result of contractions and bends. The following assumptions are made to simplify the analysis for all geometries unless otherwise specified. The void fraction of the homogenous twophase mixture is assumed constant over the feature (i.e. no phase change). Separation of the two phases occurs and the use of general singlephase frictional loss methods are no longer valid. The following correlations, from Collier (1972), are presented to calculate the static pressure drop, Equation (545), and the frictional pressure loss across a contraction, Equation (546). A simplified momentum balance for the combined flow yields PI 2 2 1 1+ (545) Ap, = 1 2 1 X (546) 21 1 where Eqluations(545) and (546) differ by a factor (1 which represents the conversion of pressure energy to theoretical kinetic energy associated with the acceleration of the fluid through the contraction. The symbol a is the ratio of the upstream Al to downstream area A2. G2 is the mass velocity of the refrigerant and is defined as the velocity at the downstream location to the specific volume at that same location. Co is the coefficient of contraction and is defined as the ratio of minimum area A, to downstream area A2. This minimum area Ac, see Figure 516, corresponds to the narrowest cross section where the smallest local pressure value is found. In order to calculate the coefficient of contraction, the twophase empirical relation presented by Ruffell (1978) according to Schmidt and Friedel (1997) is used. The equation for the contraction coefficient can be written as 11 C, =1 (547) 2.080 \1 +0.5371 Equation (547) has been compared against the contraction coefficients for turbulent singlephase flow presented by Perry (1963) in Table 54. It should be noted that both models have been determined experimentally. It has been found that modeled pressure drop across sudden contractions is satisfactory and that the constant void fraction assumption is not necessarily accurate (Collier (1972)). Upon exit from either the 90o bends or the expander cavity, sudden enlargement may exist in which further pressure losses are realized. For a twophase mixture, the change in static pressure and total frictional pressure drop across the enlargement can be determined from a simplified momentum balance for the combined flow written as p2 p1 = G2G10~ aV, 1+ x" (548) Ap, =, (1 )2 Vp 1+ x (549) where G1 is the mass flux upstream of the sudden enlargement. The homogenous and constant void fraction pressure drop models presented above may yield satisfactory predictions since low mass velocities and pressures are expected. In the case of twophase flow through a sharp edged orifice, the discharge coefficient is equivalent to the contraction coefficient if small amounts of frictional dissipation and velocity profile effects are neglected (Collier (1972)). The pressure drop equation that results from a simplified momentum balance, assuming a homogenous mixture and constant void fraction through the orifice, must be modified using a two phase multiplier The pressure drop in a uniform flow area, 90o bend can be calculated from the following equation presented by Collier (1972) 2i 8t=1 pBp P (550) where APf and AP, are the pressure drops for the liquid and vapor phases and are defined mil (1 X)2 V Ap = (551) 2CD2A2 Ap, = C2 (552) where the discharge coefficient CD is approximated as the coefficient of contraction Cc from Equation (547). This assumption neglects the small amount of frictional dissipation and velocity effects that may be incurred during the flow. The constant C is evaluated from the following general expression C="i ii V+(C 05 051[ 05f, v ,1 (553) D D where h=1 and the constant C2 is C, = 1+ 35 for 90o bends or C2 = 1+ 20 for 900 L L bends with an upstream disturbance. Conventional Inlet to Expander Cavity As mentioned previously, this inlet port is typically machined into the stator cylinder. The inlet port spread is a design parameter with significant impact on the volumetric efficiency and thermodynamic performance of rotaryvane technology. This may be of greater concern in twophase expanders since pressure drops in twophase flows are inherently larger and necessitate the formation of vapor. Depending on several factors including the spread of the intake port, the angle between successive vanes and the angular location of the leading vane relative to the intake port, the intake manifold will be in continuous contact with one or more of the expander cells. It should be noted that due to this continuous contact pulsation effects are negligible. It is hence of importance to calculate the actual mass flowrate of incoming refrigerant into each cell and the impact it may have on the performance of the expansion device. An optimal design of the intake port would minimize flow restrictions that would alter flow characteristics by maximizing the available flow area at each angle of rotation. This would ensure that an equal velocity is obtained at every opening. To capture the effect of irreversible losses that are inherent in the intake port due to flow restrictions, the concept of the discharge coefficient must be introduced. In general the discharge coefficient is defined as the ratio of the actual to ideal mass flowrates. The discharge coefficient is a strong function of the area ratio and the Reynolds number of the flow. The flow through the conventional intake port can be modeled as that of a two phase flow through a sharpedged orifiee. In the case of twophase flow through a sharp edged orifice, the discharge coefficient is equivalent to the contraction coefficient, Equation 547, if small amounts of frictional dissipation and velocity profile effects are neglected (Collier, 1972). A schematic of the three phases of vane orientation that occur during the intake process are shown in Figure 517. It can be shown that the time rate of change of volumes on either side of the leading vane in phase I, for example, differ significantly. This alters the amount of mass that enters either control volume. The throat that is formed in phases I and III constitutes a maj or flow restriction. The definition of the discharge coefficient may be altered to incorporate the effect of the formation of the throat as well as the discrepancy in the time rate of change in expander cavity volume. An area averaged, change in volume weighted component is incorporated into the definition of the discharge coefficient as such AV 4 A(8) cd(e = Cc (8) (554) A V2 A, where Aref is a reference area that denotes a frictionless orifice area that produces an ideal massflowrate. Figure 518 shows the variation pressure within the expander cavity as a function of the angular displacement of the leading vane for the ideal and actual (throttling only) cases. It can be seen from Figure 518 that a significant drop in pressure is realized in the intake and expansion phases. This dramatically reduces the expander's performance by reducing the volumetric efficiency and generated torque and power. For all else equal, the volumetric efficiency is defined as the ratio of the actual density at the cutoff volume to ideal density (i.e. inlet density). The variation in the volumetric efficiency, final pressure in the expander cavity at the maximum volume, are tabulated in Table 55 for various intake angles. Standalone experiments are needed in order to accurately determine the variation of the discharge coefficient. One discrepancy that may exist is that at smaller local rotation angles, the discharge coefficient may in fact approach unity and decrease in a near linear fashion. This trend is represented as the dotted line in Figure 518. This situation arises from the fact that both the time and volume required to be filled initially is very small and that the extremely small throat area provides for a entrainment free jet of working fluid to fill the expander cavity in question. At larger angles of rotation, there may exist entrained fluid that disrupts and alters the flow. It should be noted that the throttling losses in the exhaust port are typically found to be negligible due to the smaller velocities associated with the exhaust fluid and the larger spread area of the exhaust port. Modified Inlet to Expander Cavity The flow of the twophase refrigerant in the intake is assumed to be homogenous and gravitational effects on the pressure drops in vertical portions of the intake have been neglected. The pressure drops associated with the work necessary to protrude the vanes has also been neglected. This may be the case since the centrifugal forces exerted on the vane due to rotation of the expander are typically an order of magnitude larger. In order to model the mass flow of refrigerant into the expander, the velocities of the fluid in the contractions, bends and enlargements, the unknowns, must be calculated. Figure 519 shows a schematic of the intake of a modified rotaryvane intake. The solution procedure entails an iterative procedure in which the pressure at location 2 must be initially estimated as the average of the known pressures at locations 1 and 5. Using Equation (545), the velocity at Location 2 may be calculated. Location 3 is denoted by an because in fact it represents 4 bends of equal flow area. For the sake of brevity they are illustrated as one. The velocities within these bends are assumed to be equal. Using Equation (550) the pressure at each of the bends can be calculated. Since the flow is compressible the quality at each one of these locations can be computed by assuming an isenthalpic process. Using Equation (548) the pressure at Location 4 can be computed since the mass velocity at 3* is known. The final parameter to be determined is the velocity at Location 4, which can be computed using Apexlt = P4U24 (555) This iterative procedure is repeated until the initial guess of the pressure at Location 2 converges to within a of the following p1 ps = Ap,,,t + Ap2oz, + Apenlarge + Pexlt (556) It should be noted that the pressure at the exit can be determined using simulation models or from experiments. The mass flowrate can be computed as thz = pu,,A,, where n=2,3*,4 Thermodynamic Model of the Actual Expansion Process In this section the effects of internal leakage losses, friction and throttling are taken into account deriving the appropriate conservation of mass and energy equations. The solution procedure is detailed. The ideal predicted pressure, temperature and mass variations in the expander's control volume are used as initial estimates when calculating any nonideal effects. The velocity and hence mass flowrate of the leakage flows via different leakage paths have already been presented. Charging Process The first law of thermodynamics, taking into account heat transfer generated by friction, frictional power losses and effects of internal leakage, can be written for the process as follows dE = O, Wb +Wi~ + minthmt + Cnflleak,n~lhleak,m, yl~eak~outhleak~.out (557) Assuming the changes in kinetic energy and potential energy are neglected dEcy=dUy. The pressure within the control volume is also assumed to be uniform. Multiplying by dt Equation (557) becomes AUJ = qf p,(Vi ) +1 W + mnthin +f C nPflneak~ln hleak~leak,outfhleak,ourt (558) Solving for the internal energy of the refrigerant at the new time step, State 2, we find m2121 + f 1, (V2 6)+ +w +n mthmtr + Cnleak~,nhleak~lm Cleak,outhleak~ouit n2? + nfleak,mn C leak,ourt (559) The density of the refrigerant at the new time step, State 2, is calculated as n+ +fnleak,mn lmeak,out pt (560) The use of REFPROP 7.0 allows the determination of the thermodynamic properties at the new state point, State 2, namely the temperature, pressure and quality. The process is repeated until the end of the charging process. Expansion Process Unlike the ideal expansion process the mass in the control volume, mov, varies depending on the magnitude of the internal leakage losses after the cutoff angle Ocs, = 8mt + 3. The density at State 2 can be determined from nt, +Cn7leak,mn Cleak,outr pt (561) An energy balance of the control volume, i.e. leakage, during the expansion process yields the internal energy at State 2 as u2_11 f 1V V w 1 lak1hekz ekotla~u (562) 2 171~~2 + le~ak,ln C nlea,out The thermodynamic properties at the new time step, namely temperature, pressure, and quality, can be calculated from Equations (561) and (562) by the use of REFPROP 7.0. This process is repeated until the end of the expansion process at a predetermined design angle of 6ex. Exhaust process The exhaust process occurs at an exhaust angle 6ex until Bend out,, + 6, Where 8out is the spread of the exhaust port and 8 is the angle between consecutive vanes. The first law of thermodynamics can be written for the process as follows dE if jb f ex r~hex +f mleak,,znhea,,zn, leak,outhleakout (563) Assuming the changes in kinetic energy and potential energy are neglected, dEcy=dUy. The pressure within the control volume is also assumed to be uniform. The refrigerant flow from the control volume is also assumed to be quasisteady and homogenous. Multiplying Equation (563) by dt and solving for the internal energy of the refrigerant at the new time step, State 2, we find m,u, +q, px (V2 V)+ +w mex he + C mleark~lnhla~n la~otlau u2 = xlek (564) m2+ mleak,ln lmeak~out The density of the refrigerant at the new time step, State 2, is calculated as m2+ mleak,ln lmeak,out p2 = (565) The use of REFPROP 7.0 allows the determination of the thermodynamic properties at the new state point, State 2, namely the temperature, pressure and quality. Expander Performance Evaluation Upon development of the geometric, thermodynamic, internal leakage, frictional, throttling and any other loss mechanism, the overall performance of a rotaryvane expander can be predicted. The following parameters describe the performance of the expander with respect to different criteria. Of primary importance to the performance of any positive displacement expansion device is the geometric (builtin) volume ratio. This parameter is defined as the ratio of volumes at the exhaust and cutoff angles respectively. The reader is referred to an earlier chapter dealing with this parameter in further detail. Along with the geometric volume ratio the geometric code developed allows for design optimization with regards to the number of vanes, location of intake and exhaust ports, statorcylinder geometry and size, rotor size and eccentricity and aspect ratio to name a few. The pressure, quality and mass variations of the working fluid within the expander' s cells are predicted by utilizing the thermodynamic model. Models for the intake and exhaust processes are used in conjunction with the thermodynamic model to determine throttling losses (termed breathing in the open literature) within the ports. These throttling losses are a primary function of port design (geometry) and spread (size). The use of these models also allows us to calculate the volumetric efficiency, resultant power ratio and efficiency of the multivane expander due to throttling losses in the intake port. The volumetric efficiency may be defined as where vint is the specific volume of the working fluid within the expander' s cell assuming no throttling losses (i.e. upstream conditions) and vo, (8,,, + 3) is the ensuing specific volume of the refrigerant if there exists throttling within the intake port. Both quantities are calculated at the cutoff angle. As the volumetric efficiency decreases, the effects of throttling significantly alter the torque generated by the pressure forces exerted on the vanes by the working fluid and hence lead to a decrease in the useful power output and efficiency of the expander. The power ratio, P,, may be defined as the ratio of the power produced when throttling is accounted for to the ideal power produced by the expander with no throttling losses. Since the mass of refrigerant contained within the cell volume of the expander at the cutoff volume may be significantly less when throttling effects are considered, it may be advantageous to define a thermodynamic efficiency based on the ratio of the expander' s actual to ideal specific work. This efficiency may be defined as TI; w tthoeP (567) where the rotational speed in both cases may be assumed equal. The volumetric efficiency of the expander limits the accuracy of this assumption. The internal leakage model developed will allow further characterization and detailed performance analysis of the expander by predicting the magnitude and direction of leakage from various cells within the expander. The direction of these losses is a function of the pressure distribution predicted by the thermodynamic model. The leakage coefficient is defined as the total leakage mass flowrate to the ideal mass flowrate through the expander I= nflk(568) Singlephase leakage within the expander increases the pressure of neighboring cells and inherently increases the work output of the expander. In the case of twophase leakage losses, the gaps through which the flow enters, produce areas from which further throttling takes place. The adjacent cell pressure may increase but so does the quality of the refrigerant within the cell. This reduces the amount of useful work that can be extracted from the expansion process. The leakage power factor, Klk, of the expander can thus be defined as the ratio of power produced by the expander accounting for leakage and throttling losses and the power produced by the expander if only throttling losses are accounted for. A thermodynamic leakage efficiency may also be defined as 1_W~k+b _W~k+b mb _I 1 )(9 wb mlkb Wb Kkl& 5b) The frictional model developed allows for even further characterization and performance analysis by predicting various frictional losses throughout the expander. These frictional losses allow for the calculation of an overall frictional torque that contributes to a frictional power loss within the expander. Viscous shear stresses due to leakage also contribute to the total frictional power loss, W, The mechanical efficiency of the expander can then be defined as W, W rm k= (570) W~k+b The aforementioned performance parameters will aid in application specific design optimization of rotaryvane twophase refrigeration expanders. Performance Variation Due to StatorCylinder Geometry One geometric design parameter that has not been discussed in a thorough manner is the geometric profile of the expander' s statorcylinder which may have been alluded to in previous sections. The variation in this parameter serves a single purpose, to increase the geometric volume ratio of the expander but must simultaneously satisfy key geometrical constraints. This section presents a more detailed discussion of the apparent advantages and not so obvious disadvantages of varying the geometric profile of the statorcylinder and key geometrical constraints that must be considered in its design. The profile of a circular statorcylinder can be described in general by at most two circular arcs. If the sealing arc is symmetric about the base line, y=180o and RS(6)=180o then the profile of the statorcylinder may be easily described by a circle. The profile of a noncircular statorcylinder can generally be described by n1 circular arcs and one sealing arc depending on the complexity of the statorcylinder profile. The centers and spreads of the circular arcs are known input parameters to the geometrical code. Figure 5 20 shows a schematic and details the nomenclature associated with a symmetric and non symmetric noncircular rotaryvane expander about the base line, 6=0. As previously shown, the performance of multivane expanders can be predicted upon development of the geometric, thermodynamic, leakage and frictional models described earlier. The geometry of the statorcylinder is a prominent design variable that can greatly affect the thermodynamic and fluid flow characteristics of a multivane expander. The performance of circular and noncircular twophase multivane expanders is herein compared. Final design choices such as intake and exhaust port location and spread will ultimately determine whether the statorcylinder is symmetric or non symmetric about the vertical plane that represents the datum. Parametric optimization is detailed here. A concise comparison between noncircular and circular expanders is presented below. From the geometrical code developed, the cell volume variation throughout the expander is predicted. For all else equal, the eccentricity of the noncircular expander during the intake process is smaller than that of the circular expander. This corresponds to a lower rate of increase in cellvolume. This lower rate of increase in cellvolume may correspond to a larger cell pressure or lower cell quality at the cutoff angle if the cell pressure during the intake process is assumed variable or uniform respectively. This can be seen when determining the vane protrusion from the rotor slot as depicted in Figure 5 21. For the same geometrical parameters, the noncircular expander has a higher geometric volume ratio when compared to the circular expander. This is a result of the significantly larger and smaller volumes corresponding to the exhaust and cutoff angles respectively. The rate of increase of the cellvolume and spread of the expansion zone are a function of the noncircular expander' s symmetry and location of the exhaust port. For a nonsymmetric noncircular expander, the angular spread of the expansion zone is greater, due to location of exhaust angle, and hence the cellvolume increase is slower. This results in lower internal leakage losses due to lower pressure differentials between adj acent cells. The symmetric noncircular and circular expanders are typically designed to have the same exhaust angle. In this case the cellvolume increase within the symmetric noncircular expander is much faster leading to a larger pressure differential between adjacent cells. The pressure distribution around the rotor' s periphery significantly influences internal leakage losses within the expander. Although the expansion ratio of the symmetric noncircular expander is significantly larger, the higher cellvolume increase within both leads to higher internal leakage resulting from greater pressure differentials between adjacent cells. As a result, a smaller lowpressure region is realized throughout the spread of the exhaust port within a nonsymmetric noncircular expander. This significantly decreases the internal leakage from highpressure regions across existing gaps between the rotor and two endplates. The spread of the sealing arc is governed by the curvature of the statorcylinder. The spread of the sealing arc of a circular expander is almost always larger than that of a noncircular expander. This corresponds to a lower pressure gradient across the sealing arc resulting in lower internal leakage across that radial clearance. In the same light, a symmetric noncircular expander has a larger sealing arc spread when compared to a nonsymmetric noncircular expander. From the developed thermodynamic model, it can be seen that the noncircular expander has a higher volumetric efficiency when compared to the circular expander. For all else equal, a lower increase in the cell volume results in less throttling during the intake process which in tumn results in a more effective filling process. This in turn results in a higher power factor. The developed internal leakage model validates the trends of leakage losses aforementioned in further detail. The higher cell volume increase of the circular and symmetric noncircular expander result in higher pressure gradients within the gap between the rotor and endplates resulting in higher radial velocities of the fluid at the rotor' s periphery. The leakage across the high and low pressure intake and exhaust regions via the sealing arc also increases as the spread of the sealing arc decreases. Leakage losses past the vane tips and the sides of the vanes, adj acent to endplates, of a multivane expander tend to be significant. The magnitude of these losses is governed by how well the vanes remain in contact with the statorcylinder by means of undervane pressure forces or springs. If all else is similar, the leakage past the vane tips in the circular expander is greater due to a higher increase in cellvolume and thus a greater pressure differential between adj acent vanes in the intake process (i.e. smaller angular displacements). This is a direct result of the larger eccentricity during the intake process when compared to noncircular expanders. This results in a greater required vane protrusion, X(6), from the vane slot. Inadequate undervane forces will hence result in larger leakage flow channels. Internal leakage past the vane sides is also a function of the pressure differential and vane protrusion and the analysis follows in the same light as mentioned previously. Although the symmetric noncircular and circular expanders exhibit approximately similar working fluid capacities, the internal leakage losses in the former are much more significant. This is a result of the larger vane protrusions necessary to maintain vane and statorcylinder contact. It is also the result of higherpressure differences between adj acent cells. Although the circular expander exhibits larger leakage losses when compared to the nonsymmetric, noncircular expander (see above) it's higher capacity (amount of mass in control volume at cutoff angle) leads to a smaller leakage coefficient (ratio of mass flow of leakage to total mass flow through expander) and hence higher leakage efficiency. The kinematic and friction models developed aid in further performance prediction and comparison between circular and noncircular multivane expanders. The number of arcs that describe the geometry of the statorcylinder greatly affect the sliding velocity and acceleration of the vanes. Since the noncircular stator is described by at least 5 arcs, there are an increased number of discontinuities and an increased rate of change in vane sliding acceleration and velocity respectively (Figure 522). At larger eccentricities, the presence of these characteristics results in larger frictional losses. For example the circular expander would exhibit larger frictional losses during the intake and latter stages of the exhaust processes due to a larger eccentricity. Due to the higher fluid handling capacity of the circular expander, and hence power output, the mechanical efficiency of this device is typically larger than that of a noncircular expanders although higher frictional losses may be realized. The choice of statorcylinder geometry is an openended design optimization problem. Fluid handling and geometric volume ratio requirements as well as physical constraints when modifying existing machinery also influence this choice. Tradeoffs due to competing effects arising from frictional losses and internal leakage losses are also expected. Heat Transfer The following conclusions were made regarding heat transfer modeling: * External insulation is deemed necessary * Order of magnitude analysis reveal insignificance relative to other loss mechanisms * Moderate temperature differences * Time available for heat transfer to/from working fluid in control volume is insufficient a ,ROTOR 1(3) \\RS(6) V~2 '2) Leading vane TATOR Trailing vane Figure 51. Schematic of nomenclature used and leakage paths of a circular rotaryvane expander with general orientation and a (a) conventional or (b) modified intake ports Table 51. Primary leakage paths in a rotaryvane expander Path Path Description Index (1) Axial gap between the rotor and the two endplates (2) Radial gap between the tips of the vanes and statorcylinder (3) Axial gaps between the sides of the vanes and the endplates (4) Radial gap between the rotor and stator cylinder, minimum clearance (5) Gap between the faces of the vanes and the side walls of the rotor' s slots (6) Axial clearance beneath the vanes and between the rotor and the two endplates P1=Pav(8) xi, T1 ui=0 Pb=Pav(8+6) Reservoir xe, Pe, Me Figure 52. Schematic of a typical leakage path 200 General Form Discretized Form d p)= 0p1u1 = Peue (56) dx d(pu2> dP2 PPA u, = m~ue (57) dx dx 23 ve dy; d u 12 U2 pu+ pu =O 0 4= h + (58) dx dx2 Table 52. Governing equations and their discretized form describing onedimensional adiabatic Fannoflow from a reservoir U=co r Pav(B) Pav(8+6) Pav(6)>Pav(8+6) Figure 53. Shear and pressure driven Couette flow Table 53. Variation of operational and dimensionless parameters to model flow in axial gap as laminar and with a zerothorder approximation Operational Parameters Dimensionless Condition Parameters 35 0 2000 1800 1600 1400 1200 1000 0 100 200 300 Angular Displacement, 6 Figure 54. Nonaxisymmetric pressure boundary condition on outer surface of the rotor Figure 55. Freebody diagram of a vane protruding outward from a rotor slot at a local angle 6 Pin Rotor 7 EndPlate rR P r,u m Figure 56. Schematic of generalized Couette flow in the axial gap between rotor and endplate 350 o 200 a 150 ...F 0 100 /F J 150 / FN 0 45 90 135 180 225 270 315 360 Ang ular Displace menst, a Figure 57. Variation of reaction forces on a vane with no vanetip curvature as a function of angular displacement 150 z ( 100 o 50 0 45 90 135 180 225 270 315 360 An g ular Disp lace me nt, a Figure 58. Variation of reaction forces on a vane with a circular vanetip profile as a function of angular displacement 0.6 0.4 0.2 0 0.2 0.4 0.6 0.8  th,in=60 deg  th,in=15 deg  th,in=5 deg 0 100 200 300 400 Angular Displacement, 8 Figure 59. Variation of leakage from/to the expander cavity as a function of angular displacement due to nonaxisymmetric flow between the rotor and stationary endplates for different intake angle spreads u,0.2 S0.1 o O LL. u, 0.1 u~a0.2 T~ k/~hrottling th,in=60 Qe 0.3Ida 0. Th rottl ing th,i n=30 1 0.5 0 100 200 300 Angular Displacement, a Figure 510. Variation of nonaxisymmetric leakage from/to the expander cavity for the ideal and throttling cases S0.015 S0.01 o 0.005 :E th, in=6 0 S0.005 ~ I ~th,in=1 5 S0.01 ca th,in=5 0.015 0 100 200 300 Angular Displacement, 8 Figure 511. Variation of leakage from/to the expander cavity through the gap between the sides of the vanes and endplates for different intake angle spreads 206 Ideal Actual .E0 1.2E03 8.0E04 6.0E04 4.0E04 2.0E04 0.0E+00 0 5 Angular Displacement, 8 Figure 512. Variation of leakage to the expander cavity from the rotor slot (modified intake) through the gap between the face of the vanes and rotor slot 3.5 2.0 1.5 1.0 0 100 200 300 400 500 600 700 800 900 1000 Expander Rotational Speed, RPMI Figure 513. Variation of the ideal and actual mass flowrates through the expander as a function of rotational speed 207 deall Actual 3.0 2.5 2.0 1.5 1.0 0.5 0.0 Numbe r of Va nes Figure 514. Variation of the ideal and actual mass flowrates through the expander as a function of the number of vanes A B Fiue 5.Cmarsn fwy ywhc fudisitrdcd no h epnerscaiy A)cneninl nae i ntk or n B oife ntk iartr lt through ~ ~ ~ ~ ~ ~e enltst nue aetpadsaorclne otc 208 Table 54. Comparisons of contraction coefficients for turbulent singlephase flow 1/o 0 0.2 0.4 0.6 0.8 1 C, Perry [1] 0.586 0.598 0.625 0.686 0.79 1 C, Ruffell [2] 0.618 0.637 0.664 0.708 0.790 1.0 % 5.2 6.1 5.9 3.1 0.0 0.0 fully developed linlet flow s r Figure 516. Flow through a sudden contraction 209 8,, AV1 AV2 I II Figure 517. Schematic of the three phases of vane orientation that occur during the intake process Figure 518. Variation of pressure in expander cavity as a function of angular displacement for the ideal and actual (throttling only) cases Table 55. Variation of volumetric efficiency and final pressure as a function on inlet angle in an expander with throttling losses accounted for No Throttling With Throttling 6,, r, Pex, kPa py% Pex, kPa py% P 5 8.704 681.48 100 432.39 52.92% 35.09% 15 5.762 878.52 100 618.86 57.31% 5.62% 25 4.134 1049.29 100 795.70 59.98% 26.59% 35 3.138 1194.38 100 955.93 63.44% 38.90% 45 2.487 1315.36 100 1096.45 65.79% 46.73% 75 1.496 1562.02 100 1402.39 71.42% 58.35% Teva=5oC, Tcond=45oC, reprocess=10.925, N,=8, Pex, kPa=584.1 2000 1800 1600 1400 1200 1000 800 600 400 200 0 0 6in+8 100 200 300 Ang ular Dis place m ent, deg Contraction ~' 1Enlareement Exit Figure 519. Schematic of the intake port of the modified rotaryvane intake through the endplates and into the rotor cavity via rotor slots Figure 520. Schematic of (a) symmetric (b) nonsymmetric noncircular rotaryvane expander comprised of four circular arcs (14) and a sealing arc (5) Circular MVE Noncircular MVE 0 '/ 0 20 40 60 80 100 120 140 160 180 200 220 240 260 280 300 320 340 360 Angular Displacement, deg Figure 521. Variation of vane displacement as function of the leading vanes' angular displacement for both a circular and noncircular MVE 2 Circular MVE  Noncircular MVE  1 E O S3 S 20 40 60 80 100 120 140 160 )0 200 220 80 260 280 300 3 0340 3( Angular Displacement, deg Figure 522. Variation of vane velocity as function of the leading vanes' angular displacement for both a circular and noncircular rotaryvane expander CHAPTER 6 EXPERIMENTAL PROGRAM This chapter deals with the experimental apparatus that has been designed, constructed and used initially by Alphonso (2003). The apparatus has been modified and extended to investigate the performance of a modified refrigeration system that includes the utilization of a twophase expander as a throttle valve replacement. This chapter describes the experimental facility, data acquisition system, the twophase expander selection and testing and the realtime control scheme by which the expander is controlled. Experimental Facility Chilled Water/Heated Water Loop The experimental facility employed in this investigation consists of a constant temperature water loop. This is accomplished by using a water chiller for cooling the water and a water heater for heating it. The system is designed in such a way that the drop in water temperature due to cooling is equal to the rise in its temperature due to heating. Figures 61 and 62 show the system used in the experiments. The water heater (Vanguard VG 0301CO9767, model no. 6E725, wattage: 4500 / 3380, capacity: 119.9 US. gallons) is used to add a constant heating load to the constant temperature water loop. The water heater employs two electricallyheated coils to heat the water. The coil temperature can be adjusted by employing electronic thermostatic controls located on the water heater control panel. The experimental procedure requires the water heater to be used in two modes of operation. The first mode, the Standard mode, was structured in such a way that the water heater provides a larger heating load to the water in the constant temperature loop. This corresponds to preset upper and lower coil temperatures of 550F and 540F, respectively, with a loF temperature differential applied to both coils. The second mode, the CutOff mode, was structured in such a way that the heater provides a comparatively lower heating load to the water in the constant temperature loop. This corresponds to preset upper and lower coil temperatures of 500F and 490F, respectively, with a loF temperature differential applied to both coils. The water heater was fitted with a blowoff safety valve to guard against undesirable pressure buildup. Figure 61 shows the water heater as well as controllers and hydronic expansion tank. The water chiller (model RTP201, 24000 BTU/hr 208230 VAC air cooled condenser) is used to chill the water as it flows through the constanttemperature water loop. The constanttemperature water loop also includes a hydronic expansion tank, besides the water chiller and the water heater. Rubber hoses and copper pipes were used to connect the water chiller and the water heater. The entire piping of the chilled/heated closed loop is well insulated to prevent heat loss/gain from and to the loop. Data Acquisition System An instrumentation map and schematic of the modified chiller used for experiments is presented in Figure 53. Temperatures were measured in the experimental facility using copper constantan (typeT) thermocouples with an uncertainty of + 0.20C. This type is suitable for low temperature applications as well as temperatures up to 3700C. The thermocouples were insulated for accuracy. Temperatures of the refrigerant as it flows through the refrigeration system were measured at the inlet and exit of the condenser and evaporator. The temperature of the air flowing through the aircooled condenser of the water chiller was also measured. In the constanttemperature water loop, the temperature of the water was measured at the inlet and exit of the water chiller tank and at the outlet of the pump. Pressure transducers (Mamac Systems, model no. PR264, accuracy fl% of the full scale) were used to measure the pressure of the refrigerant at five locations in the refrigeration system. These transducers were calibrated to give an output of 05 VDC to the data acquisition board corresponding linearly to a pressure range of 02000 kPa. The transducers were calibrated using a Calpal hand held pressure calibrator. These transducers were used to measure the refrigerant pressure at the inlet and outlet of the condenser and evaporator. Air humidity at the inlet and exit of the aircooled condenser was measured using a humidity transducer (Mamac Systems, model no. HU225, accuracy f3% of the full scale). The transducers were calibrated to give an output of 05 VDC to the data acquisition board corresponding linearly to a relative humidity range of 0100%. The refrigerant mass flowrate as it flows through the chiller was measured using a flowrate transducer (Sponsler Co., Inc., model no. SP7113). This transducer was calibrated to give an output of 05 VDC to the data acquisition system corresponding linearly to a flowrate range of 0 47.4293 lbm/min. The water loop mass flowrate was measured using a flowrate indicator (Sponsler Co., Inc., model no. SP3/4CBPHLA 4X). The water flowrate was read off the digital display of the transducer. Compressor power was measured employing the voltage and current transducers across the compressor motor. The voltage was measured using a voltage transducer (FlexCore, model no. AVT300CX5, accuracy f0.25%), which was calibrated to give an output voltage of 05 VDC to the data acquisition board corresponding linearly to a range of 0300 AC line voltage. The current flowing through the compressor motor coils was measured using a current transducer (FlexCore, model no. CTD025A, accuracy +0.5%), which was calibrated to give an output voltage of 05 VDC to the data acquisition board corresponding linearly to a current range of 025 Amps. The outputs of the various transducers were inputted to a data acquisition board (CIOEXP 32), which is connected to another data acquisition computer card (Measurement Computing, model PCIDASO8) located in the computer. A computer equipped with stateoftheart data acquisition software LABVIEW 7.1 was used to record the data. The location and type of instrumentation used are shown in Figure 63. Unmodified Chiller Experimental Procedures Testing was performed for the unmodified chiller unit for the standard and cutoff modes of operation. The standard mode operating conditions were structured in such a way that the heater provides a larger heating load to the water in the constanttemperature water loop. This corresponds to a temperature setting in which the upper and lower coil temperatures are 550F and 540F respectively, with a loF temperature differential applied to both coils. The cutoff mode conditions were structured in such a way that the heater provides a lower heating load to the water in the loop. This corresponds to a temperature setting in which the upper and lower coil temperatures are set at 500F and 490F respectively, with a loF temperature differential applied to both coils. The chilled water exit set point temperature was kept at 430F throughout testing. The water flowrate in the loop was kept constant by regulating the flow through a gate valve to a preset level according to the required cooling capacity considerations. All test runs were conducted under similar ambient conditions for a period of 6 hours. A data point was a result of averaging readings at the rate of 1 Hz for a 60 second time interval. Figures 64 to 68 represent sample runs of the chiller in both modes of operation for a period of 6 hours. States 1, 2, 3 and 4 represent the inlet to the compressor, condenser, throttle valve and evaporator, respectively. Dynamometer Selection, Data Acquisition and RealTime Control Scheme According to data collected from a parametric analysis of the basic vapor compression refrigeration cycle, see Table 61, the size of the dynamometer was determined. The size of the dynamometer is a function of the anticipated power output of the expander. According to a parametric analysis that was conducted, a dynamometer with a rating of 375 watts was deemed adequate. This rating represents an overestimate of the maximum power output for ideal and actual vapor compression cycles utilizing ideal twophase expanders operating at 4oC and 45oC evaporator and condenser temperatures, respectively. A hysteresis type dynamometer cooled by means of compressed air was selected. This versatile dynamometer was deemed to be the ideal type for testing turbomachinery with relatively low power outputs after numerous consultations with leading dynamometer manufacturers. A LabVIEW code was written to acquire and graphically present data collected by the instrumentation. The LabVIEW code also extrapolates and determines the degree of superheat of the fluid leaving the evaporator in order to adjust the mass flowrate through the expander. An integrated closedloop highspeed programmable dynamometer controller adjusts the torque applied to the shaft of the expander. This controls the flow rate of refrigerant through the expander and ensures an appropriate degree of superheat at the compressor suction. Figure 69 shows a schematic of the proposed control system and algorithm. In order to determine the corresponding saturation temperature at a given evaporator outlet pressure, the following equation proposed by Bachr and TillnerRoth (1995) was solved iteratively using the NewtonRaphson method. Equation (61) can be used for both R22 and R134a with the appropriate constants in Table 62 P(0) 1 1 Pc j;1 8 [nB a8 46+,~ 6 where Pe = Critical Pressure of the Refrigerant 6 = Dimensionless Temperature, O = 1 To = Critical Temperature of the Refrigerant and the coefficients can be found from Table 62. The solution procedure to determine the degree of superheat can be described as follows: * Express Equation (61) in the form f(B, P) = 0 . * Input the Pressure, P(6), into Equation (61) at which the corresponding saturation temperature is desired. * Input an initial guess as to what that saturation temperature is and calculate the corresponding dimensionless temperature, 8o. * Compute the Derivative of Equation (61) with respect to the dimensionless df (B, P) temperature, and use the NewtonRaphson method to find a new dB f (B, P) estimated value for 6, O = 8, f '(B, P) *Continue process until convergence. Rotaryvane Expander Selection This section details the different choices of rotaryvane type turbomachinery that have been modified and used as twophase expanders. Modified Automotive Airconditioning Compressor A doubleacting rotaryvane automotive A/C compressor of unknown capacity at the time of purchase due to proprietary restrictions was obtained. The automotive compressor was deemed appropriate after several unsuccessful attempts of contacting compressor manufacturers for residential and industrial refrigeration systems. Automotive compressors are typically designed for volatile working conditions and may be difficult to modify. Modifications to the piping to/from the compressor housing could also be difficult to modify. Rotaryvane compressors were used extensively in the late 80s and early 90s by automobile manufacturers such as BMW and Mazda. The rotaryvane compressor selected and purchased is a rebuilt A/C compressor that runs on R12 and can be retrofitted to work with R22 and R134a. After conducting research dealing with the modifications that must be done in order to operate it as an expander, the modifications deemed necessary included changing fittings, Orings, and the reed valve. Internal leakage losses associated with this modified A/C compressor were initially thought to be less than leakage losses associated with other type of modified turbomachinery due to the typical existence of tight tolerances and need for significantly efficient compressor designs. Performance of Modified Compressor Upon operation of the modified system with the expander installed, the expander was found to perform unexpectedly. Further examination of the internals of the expander revealed that sealing problems associated with the deformation of two Orings may have been the cause. These Orings seal the high and low pressure pockets within the compressor/expander (Figure 610). Observation of the Orings, upon completion of several tests in the refrigeration system, showed signs of elastic deformation. Tests with compressed air were conducted after which it was determined that the inadequate sealing provided by the Orings may not be the only cause of the unfavorable performance of the expander. Problems associated with the startup operation (as defined below) of this expander were then investigated. It was found after further examination and testing of the internal cavity of the expander that significant centrifugal force due to rotation is necessary to maintain continuous contact between the vanetips and the statorcylinder. Although pressurizing slots and a means for pressurized fluid to enter the slots exist for compressor operation, there is no guarantee that the high pressure fluid enters the pressurizing slots when run as an expander. This lack of contact is believed to be the primary cause of the expander' s poor performance since insufficient vane protrusion would hinder the development of adequate torque from the incoming working fluid acting on the vanes. To overcome this, a mechanically driven coupling was used to drive the expander shaft to generate sufficient centrifugal force and help eliminate any startup issues. Secondly, prototype mechanical springs, in the form of leaf springs, were designed and machined out of tempered spring steel and tested in the vane slots. Leaf springs were determined to be the most suitable type of spring for this application because of both the dynamics of the application and the dimensions associated with the vane slots. Three different configurations of the vanes were machined in order to determine the optimum vane geometry to ensure vanestator contact with the help of leaf springs placed in the pressurizing slots. Upon installation in the expander initial testing revealed that the modified vanes did very little to enhance the performance of the expander although continuous contact between the vanetips and statorcylinder was maintained. One possibility the expander did not function as expected is the internal flow path arrangement (Figure 611). Since the current expander was initially designed as an automotive airconditioning compressor, the dual flow path configuration of the compressor is not ideal for expansion. Upon testing the expander with refrigerant, the shaft of the expander would operate as if the shaft were locked. This resistance to motion was deemed to be the primary result of the compression of liquid due to poor geometrical design of the intake or exhaust ports. Further analysis of the symmetric, elliptical double acting rotaryvane compressor revealed that the minimum tolerances that exist between the rotor and elliptical statorcylinder were approximately 25 Clm (0.001"). The temperature differential between the intake (high side temperature) and the exhaust (evaporator temperature) may have also caused the rotor to lock due to material thermal expansion of either the statorcylinder or rotor. Further experimental measurements are needed to prove this. This also supports the conclusion that an alternate flow path was needed to eliminate any unwanted liquid compression and material thermal expansion that may take place. An alternate flow path configuration would also eliminate the extremely "tight" tolerances that exist between the rotor and the statorcylinder at the minimum clearance. Design Issues Several design issues were deemed responsible for the inadequate operation of this modified double acting compressor. They include the following: * Unsuitable volume ratio as determined from a modified geometrical code. * Intake port spread of 8in=10o. This results in significant throttling losses in the intake port. This compressor exhaust port is a sound design choice. * Overlap between intake and exhaust ports. Since the compressor has 5 vanes (6=72o) there exists an approximate 650 overlap (accounting for vane thickness) that is responsible for excessive leakage past the minimum clearance on either side of the rotor. A significant driving potential drives this. * Minimal clearance is 25 Clm. Significant pressure and temperature differentials on either side of the minimal clearance cause thermal expansion of the materials that results in the "locking" of the expander shaft. * Poor design of exhaust port as an expander. Retrofitting the ports is difficult due to the hermetic nature of the compressor. Designed and Machined Expander The design, fabrication and testing of a machined rotaryvane expander was deemed to be the next most reliable and suitable alternative. It would also aid in understanding the complex factors involved in selecting geometric design choices for this specific application. Many factors were taken into consideration when making this decision and they included: * The ability to design the rotor and statorcylinder. During this process the geometric volume ratio of the expander would be optimized to allow for complete expansion of the refrigerant and to avoid under and overexpansion. The dimensions of the cylinders are constrained by the dimensions of the dynamometer. * The ability to design the flow path of the refrigerant. This would ensure proper expansion of the refrigerant and avoid compression and additional pressure losses which may result from poor flow path design. These inefficiencies would reduce the amount of power that may be recovered from the system expansion process by means of an expander. * The ability to optimize the location and the spread angles of the intake and exhaust ports. This provides an additional degree of flexibility when optimizing the geometric volume ratio of the expander. * Ease of installing instrumentation. Locations for different measuring devices, primarily pressure taps and thermocouples, would be taken into consideration. This would allow for a more extensive comparison of theoretical and experimental results. * Both the size and the weight of the expander may be optimized. * The ability to design and fabricate the vanes. The design would account for the addition of mechanical springs if needed. These springs would keep the vanetips in continuous contact with the statorcylinder. Either compression or leaf type springs may be utilized with appropriate modifications to the vanes and rotorslots made. In order to ensure the adequate design of a rotaryvane expander, the geometric volume ratio of the expander must be as close as possible, ideally (see Chapter 5 in regards to over and underexpansion), to the process volume ratio. Adequate selection of the expander' s dimensions ensures an appropriate value of the expander' s geometric volume ratio suitable for the use of this rotaryvane expander as a throttle valve replacement in vapor compression refrigeration systems. Other primary variables that will play a critical role in the performance of this expander include the intake port arc length and width, the exhaust port location, depth, and contour, the number of vanes and the aspect ratio of the rotor. Other variables that effect the design of the expander and can lead to poor performance of the expander include bearing design and location, rotor dynamics and the method by which the vanes will maintain continuous contact with the statorcylinder. All of the aforementioned design variables have been addressed thoroughly and a preliminary designs of the expander was developed with the aid of recent literature and commercially available rotaryvane type turbomachinery. Adequate tolerances between the various moving parts were allotted to ensure proper lubrication and a reduction in internal leakage and frictional losses. The tolerances were calculated to ensure that internal leakage losses are minimized. Springs were preliminary deemed to be unnecessary due to adequate centrifugal forces that are expected in this new design. Generated centrifugal forces are needed to maintain continuous contact between the vanetips and the statorcylinder. Sizing, selection and the mounting locations of two bearings were also carried out. Conventional shielded ball bearings were selected since they are inexpensive and are rated for at least 1,000 lbs in both the radial and axial directions. According to preliminary estimates of the forces that are expected the rating aforementioned should suffice. Initial performance tests performed with compressed air and refrigerant revealed that leaks from the shaft penetration were still significant. The original dimension of the endplate (shaft side) was modified and a sealing disc was designed to be bolted to the endplate. The sealing mechanism that was conceived for this application consisted of a tapered sealing disc that would be bolted to the modified endplate. The gaps that exist between the tapered disk and the shaft are sealed with general purpose Teflon compression packing. Further performance testing showed a significant decrease in the amount of refrigerant/air that leaks. Performance of Machined Expander Further testing with compressed air revealed that there exists a critical pressure differential between the inlet and exhaust states required to overcome the inertial mass of the expander and vanes and any starting friction between any of the sliding or moving parts. During testing of the newly designed expander in the refrigeration system, it was apparent that the shaft of the expander didn't lock as was the case with the first expander tested. However, the newly designed expander didn't function as desired due to significant external leakage. This would deem experiments unrepeatable and cause excessive uncontrolled refrigerant leakage to the ambient. The design of the expander was modified to eliminate leakage losses that are primarily due to imperfections in the current rotaryshaft seal design. Additional research and possible design/selection of commercially available rotary shaft seals was deemed necessary but beyond the scope of this investigation. Other factors that may cause this undesirable performance is the fact that the expander's internal size and weight (sliding and moving parts) play critical factors in effecting the value of the critical pressure difference necessary to start the expander. The performance characteristics of interest for the twoton aircooled chiller used as the basis for this experimental program are limited. These parameters include, but are not limited to, the mass flowrate of the refrigerant, the pressure differential between the highside and lowside and the thermodynamic state properties at the exit state of the condenser. The parametrical relationship that must be satisfied in order for the expander to operate is that the expander displacement must match the experimental volumetric flowrate of the refrigerant in the refrigeration system. Modified AirMotor A properly sized, 4vane, circular GAST airmotor was then tested as an expander. The inlet ports are engineered in such a way that adequate undervane pressure from the incoming refrigerant helps provide for continuous contact between the vanetips and statorcylinder. This also eliminates severe throttling losses that may arise due to a short inlet port spread. This is typically the case in conventional expanders, where the fluid is introduced directly into the expander's cavity. As mentioned previously, the inlet port spread is among the most influential geometrical design choices which affect the geometric volume ratio of a rotaryvane expander. The geometrical characteristics of this unmodified expander were found to be unsuitable for the purpose of its use as an expansion device. Table 63, shows 12 proposed modifications, a maj ority of which have already been machined, in order to optimize the geometric volume ratio of the expander. Several constraints, namely the vane height, maximum protrusion from the vane slot, machining complexity and mechanical strength have been addressed to yield parametrically optimized design parameters using the models developed to yield a maximum volume ratio. It should be noted that the inlet start parameter denotes the angular location relative to the datum at which the intake process begins. In conventional designs, and previous work, this was Oo. In this design, the intake process begins at 55o. It should also be noted that the angular locations of the cutoff (minimum) volume V1 and the exhaust (maximum) volume V2 are alSo presented. The angular location of the cutoff volume is the sum of the inlet start location, angle between successive vanes 6 and spread of the inlet port 6in. The angular location of the exhaust volume is a design parameter that typically corresponds to the location of maximum volume. The ratio of the maximum to minimum volume is defined as the geometric volume ratio. It can be seen that the unmodified circular expander's geometric volume ratio is unity due to a very large inlet port spread (6in=90o) and 4 vanes (6=90o). It has been previously shown that the geometric volume ratio increases as the number of vanes increase. Four additional vane slots were machined into the rotor as well as the angular holes that supplied the incoming fluid into the expander's cavity. This modification alone had a detrimental effect on the volume ratio since the location of the exhaust port in a circular expander is 1800. Hence the unmodified expander' s exhaust port begins in the region of compression that follows the angular location of maximum volume. It can be seen that the geometric volume ratio of the circular expander increases as the inlet port spread is decreased (case 2) and the location of the exhaust port is changed (case 3). Further reduction in the intake port spread (case 4) leads to an increase in volume ratio, but ultimately the extremely small eccentricity that exists between the rotor and stator cylinders limits the amount of expansion that can be achieved. It should also be noted that only 15% of the vanes' total height protruded from the vanes' slot. It was found that the complexity of machining modified endplates and reducing the size of the rotor made machining a noncircular stator cylinder very attractive. These alternate designs can be seen in Figure 612. Case 5 represents the first use of a machined symmetric noncircular stator cylinder. Optimized geometrical parameters from earlier test cases were used. For the symmetric noncircular case, the maximum expansion volume occurs at the angular location of 2200 (1800). It should be noted that the values listed in Table 63 correspond to a generally oriented circular expander, the basis of the design code developed. The extent that the statorcylinder could be machined was constrained by an adequate sealing thickness as well as the minimum vane height in the rotor slot necessary to maintain adequate operation of the expander. This percentage was found to be approximately 20%. By comparing cases 5, 6, 7, 8 and 9, it was observed that the angular location of the intake port start has a tremendous impact on the geometric volume ratio of the expander. This arises due to the fact that the angular location of the cutoff volume decreases as the location of the start of the intake port decreases. The current design introduces the fluid into the expander cavity via a 250 angular cut in the rotor. This requires the intake port start to be no less that 250. This ensures that the fluid is not introduced into the minimum volume encountered during the sealing arc spread or directly into the exhaust port. Further increase in the geometric volume ratio can only be attained if a non symmetric noncircular statorcylinder is used. The maximum geometric volume ratio obtained is 7.3 (case 12) whereas it is 3.86 (case 7) for the symmetric noncircular expander. The rate of increase of the volume in a nonsymmetric noncircular expander is substantially less than that corresponding to the symmetric noncircular expander and hence a larger geometric volume ratio can be achieved. SinglePhase Experiments In this section the objectives, experimental setup and results of the singlephase tests that have been conducted are described. The obj ectives of these experiments included the verification of the feasibility of using rotaryvane turbomachinery, air motors and compressors, as expanders. In order to do so, the thermodynamic and fluid mechanic characteristics of both the rotaryvane airmotors, compressors and expanders were analyzed. The optimum geometrical and operational characteristics of each machine are presented. Experiments were conducted to understand the working principles and operational constraints of each machine. This study also helps formulate design concepts that can be utilized to modify airmotors or compressors into optimized expanders for single phase flow applications. The experiments will be used to predict and evaluate modifications made to geometrical parameters such as the optimum intake and exhaust port locations, their spreads and the geometric volume ratio as well as resulting performance parameters such as the work produced, isentropic and volumetric efficiencies. Experimental expertise, including proper assembly and sealing, of rotary vane turbomachinery is also expected to be gained and may improve performance and operation significantly. Singlephase experiments with compressed air and liquid/vapor R22 were carried out on a benchtop experimental setup with various modifications to a commercially available rotaryvane airmotor. Dry compressed air supplied to the building is used to test the device. Saturated vapor or liquid R22 may also be fed into the expander from a canister that is in equilibrium. The elevation and orientation of the canister relative to the expander is important as they determine the state of refrigerant that exits the canister. The refrigerant used enters the expander from the high pressure supply tank and exits the expander into an evacuated reclamation tank. Depending on the duration of the test necessary, the reclamation tank can be maintained at a vacuum pressure maintained by a vacuum pump. Depending on the geometrical parameters chosen, the device can operate as an expander. The thickness of the gaskets and rotaryshaft seal design were altered, when necessary, to accommodate higher working pressures than those recommended by the manufacturer. The commercially available airmotor is of the nonlubricated type. The addition of lubrication oil to the working fluid may ensure proper lubrication, sealing and operation. The inlet and outlet pressures can be adjusted by a pressure regulator and a valve, respectively. Pressure gauges or transducers, thermocouples, mass flowrate meter (rotameter), are installed at the inlet and outlet locations where necessary. The shaft of the expander is coupled with a hysteresis type dynamometer. The dynamometer is interfaced with a high speed programmable dynamometer controller which displays the actual amount of mechanical power extracted, torque produced and rotational speed of the expander. The controller may be interfaced with a computer to provide a continuous data stream. The controller is operated in the openloop mode. In this mode the user has complete control over the braking load, produced by the dynamometer, by which the torque and speed of the expander are varied. Figure 613 shows a schematic of the single phase experimental setup. In the following sections, the results of numerous tests are summarized. In certain instances, inadequate operation or complexities are explained. Summary A rotaryvane airmotor with an adequate volume displacement has been retrofitted to an expander by changing the internal geometry of the device, namely the inlet port arc spread and start, start of exhaust port and the number of vanes. The geometry of the statorcylinder is also very critical to the thermodynamic performance of the expander. A noncircular statorcylinder has hence been machined. This statorcylinder is symmetric about the vertical base line of the expander. The maximum volume ratio that could be achieved with such a configuration is 5. Further analysis showed that with a non symmetric noncircular statorcylinder, the volume ratio can be increased to approximately 7.5. In order to avoid time delays that may result from the manufacturer in case a new airmotor is needed, experimental testing and confirmation is needed before the nonsymmetric, noncircular statorcylinder is machined. A maj or source of problems, external leakage, has been solved. The use of modified gaskets (both material and thickness) and a modified rotary shaft seal have ensured adequate sealing of the expander well beyond the rated pressure of 689 kPa. Additional time and effort has been spent to avoid the manufacture of a costly and heavy external enclosure. The condenser is expected to operate at a pressure as high as 1.75 MPa. Initial tests in isolation with both air and refrigerant have yielded positive results in regard to the operational speed, sealing and change of state across the expander. The test setup could be varied to increase/decrease the operational pressure ratio across the expander. Startup problems were also not obvious, in any of the test cases, since adequate undervane pressure from incoming refrigerant helps provide for continuous contact between the vanes and statorcylinder. Difficulties arising from the operation of the modified chiller with the expander installed have hindered the progress of gathering experimental data. These difficulties, namely, arise from controlling the back pressure (i.e. evaporator pressure) when the expander loop is opened. The back pressure has a significant effect on the expander intake and hence the operation of the expander. A low range (0827 kPa) pressure regulator was used downstream of the expander to provide a means for both the control of the evaporator pressure and adequate operation of the refrigeration system. This also negates the need for the conventional expansion valve to run in series with the expander. The regulator doesn't and cannot, however, directly provide any means of control of the back pressure. These operational difficulties must be addressed. It is interesting to note that no previous work can be found in the open literature that discusses any operational difficulties that may arise. The chiller' s operational parameters were then varied in order to simulate operating conditions of interest to the funding agency. These operating parameters are namely higher condensing temperatures and system mass flowrates. These parameters were varied in order to provide measurable experimental data that may be used to validate the analytical models developed. In order for the rotaryvane expander to exhibit adequate operational characteristics, a necessary pressure drop is required across the expander. One way of controlling the pressure drop across the expander is by varying the mass flowrate of refrigerant in the system. Assuming that the twophase flow of refrigerant leaving the condenser is fully developed and turbulent (and ReD > 2 x 104 ) and that the pipe surface is approximately smooth, the friction factor, pressure drop and mass flowrate may be expressed as f =0.184Re~/ (62) Ap = f pu x (63) 2D xD2 mi = pus (64) Combining Equations (62), (63) and (64) we find that Ap ~ Cril9/5 (65) where C is a constant. It can be seen that the pressure drop across any device scales approximately to the second power of the mass flowrate through that device. Retrofitting the current experimental setup with a larger compressor, which would in turn increase the mass flowrate, is both cost prohibitive as well as potentially problematic or even catastrophic. This is a result of increased system pressures and working fluid velocities that the undersized components and piping may realize. A more promising alternative is to change certain system parameters that would in essence alter the backpressure that the expander exhaust senses. In one particular study in the literature (Badr et al. 1985), the mass flowrate of cooling water through the condenser of an Organic Rankine Cycle was varied. The authors claim the ability to vary the operational pressure ratio from approximately 2.2 < Pin/Pex < 4.3. The magnitude of change of the cooling water mass flowrate through the condenser has not been reported. In a similar manner, a reduction of the backpressure in a vaporcompression refrigeration cycle could be achieved by varying the mass flowrate of hot water through the evaporator. Initial tests with the experimental rig used have validated the general trends one should observe if the load is decreased. At the same time initial tests revealed the capacity of the hot water heater and pump, i.e. loading equipment, may not be suitable enough to achieve the operational pressure ratios necessary. Preliminary thermodynamic analyses also predict several system level changes. Further analysis is required to determine the validity of the use of this alternative as a means of regulating the back pressure that the expander exhaust senses. This methodology was deemed attractive for larger refrigeration systems. It was concluded that the variation of the backpressure is unpractical and is not responsible for the inadequate operation of the modified airmotor. Excessive internal leakage losses were deemed the cause of this failure. Comprehensive singlephase tests were carried out with the intent of determining an approximation of the performance and leakage flowrate through the modified airmotor. Static leakage tests were conducted on the four vane airmotor in a series of tests to eliminate the leakage paths discussed in Chapter 5. An order of magnitude analysis was made with the aid of the computer program developed. It was found that the leakage due to the radial clearance between the rotor and statorcylinder, axial gap between the rotor and endplates and that between the sides of the vanes and the endplates accounted for almost 95% of the leakage losses. In order to simulate the dynamic conditions typically realized within the expander, leaf springs were used to maintain continuous contact between the vanes and the stator cylinder. Further testing was done in order to experimentally investigate the sources of internal leakage. The leakage paths were blocked or altered consequentially to determine the magnitude of each path. The results of this singlephase experimentation revealed the leakage past the axial gap between the rotor and endplates was most significant followed by the leakage past the minimal clearance. The leakage flows from the other paths were found to be insignificant in comparison. This is the case when continuous contact is maintained between the vanetips and the statorcylinder. These results confirmed the conclusions made based on the developed internal leakage model. The magnitude of internal leakage flowrate were significant when compared to the ideal mass flowrate through the expander. The relative magnitude of internal leakage can be decreased if a larger refrigeration system is used. These trends are discussed in detail in Chapter 7. (1) 110 gallon water heater (2) Hydronic Expansion Tank (3) Temperature Controller (4) Control Panel (5) Pressure Relief Valve (6) Flow Measuring Device Figure 61. The water heater used to add a constant heat load to the constant temperature water loop Figure 62. Unmodified two ton aircooled barrel type water chiller Comp essed DLExpansion P: Pressure transducer Eaoao T: Thermocouple M: Massflow rate meter Q: Volumetric flow rate meter A: Current transducer V: Voltage transducer T H: Humidity transducer D&L: Dynamometer & Loadcell o iae from Heater Figure 63. Instrumentation map and schematic of the experimental setup for a vapor compression cycle with a bypass loop for rotaryvane expander integration ~ .~hc~~*nMIV~LhrF~lhOl __ ~~ ____ I _ _ _____ ~_ I__ _____________ __.__ 1600 1400 1200 1000 800 600 400 P2 P3 P4 P1 20 0 0 0 50 100 150 200 250 300 350 Time, minutes Figure 64. Variation of the measured pressure for the standard mode of operation in the unmodified chiller as a function of time 90 80 60 50  40  30  20 T2 T3 T4 T1 O 50 100 150 200 250 300 350 400 Time, Minutes Figure 65. Variation of the measured temperature for the standard mode of operation in the unmodified chiller as a function of time 1400 1200 1000 800 600 400 200 P2 P3 P4 P1  0 10 10 20 5 0 5 0 ie iue Figure 66. Variation of the measured pressure for the cutoff mode of operation in the unmodified chiller as a function of time  T2  T3 T4  T1 0 50 100 150 200 250 Time, minutes 300 350 400 Figure 67. Variation of the measured temperature for the cutoff mode of operation in the unmodified chiller as a function of time  h.l ~h.ne L ~ . ~~ h 2500 16; 2000 S1500  S1000  500  0 Standard Mode  CutOff Mode Time, minutes Figure 68. Variation of the compressor work for both the cutoff and standard modes of operation in the unmodified chiller as a function of time Table 61. Experimental Thermodynamic State Points Exp. Data Points with 6.60C of subcooling State P, kPA P, psia T, OC 1 579.3 84.0 13.9 2 1593.7 231.1 78.1 3 1574.2 228.3 34.5 4h 755.9 109.6 16.1 4s 755.9 109.6 13.5 4a nexp=25% 755.9 109.6 13.5 Process r, T, OF 57.0 172.6 94.1 61.0 56.3 56.3 Quality SH SH SC 0.136 0.127 0.134 h, kJlkg p, kg/m3 Wex, W 242.3684 242.3684 240.7814 241.9717 1154.006 202.26 202.31 204.85 5.71 64.24 5.70 16.06 5.63 32.12 5.56 48.18 5.49 4a exp=50% o 4a exp=75% o 755.9 755.9 109.6 13.5 56.3 0.132 241.5749 207.5 109.6 13.5 56.3 0.129 241.1782 210.23 *avg conditions T1: Tsat=4.740C and d~superheat=9.1560C T3: Tsat=41.070C and dTsubcool=6.60C Comp. Effic. 0.73 4h: isenthalpic expansion (TXV) 4s: isentropic expansion (Expander 100% eff) in computing 4a: mdot, g/s mdot, lblmin Expansion with irreversible expander, 25%, 50% and 75% eff) 40.48 5.34 V(m3 /S)= m2(/cg/s)v(m3/g Vdot(m3/s) 3.51E05 Process Volume Ratio r,: Ratio of densities at condenser outlet and evap inlet Table 61 Continued. no subooling State P, kPA P, psia SAME SAME Process T, OC T, OF Quality h, kdlkg p, kg/m3 Wexp, W 3 1574.2 228.3 41.07 105.926 sat L 251.08 1123.8 4h 755.9 109.6 13.52 56.336 0.181 251.08 158.33 4s 755.9 109.6 13.52 56.336 0.169 248.81 158.35 91.89 4a 25% 755.9 109.6 13.52 56.336 0.178 250.51 160.6 22.97 4a 50% 755.9 109.6 13.52 56.336 0.175 249.95 162.94 45.94 4a 75% 755.9 109.6 13.52 56.336 0.172 249.38 165.35 68.92 7.10 7.10 7.00 6.90 6.80 Cool Compressed Air Multivane Expander By pass Loop Evaporator Extrapolate degree of superheat (SH) from or erties subroutine coded I ino LaVIEWP: Pressure transducer T: Thermocouple D&L: Dynamometer & Loadcell Is S>10C? P w/DAQSC: Signal Conditioner DAQ: Data Acquisition Board FalseTrueCent: High Speed Controller Increment torque Do not application on change dynamometer speed Figure 69. Schematic of the cutaway view of the bypass loop and evaporator and the logic behind the continuous control scheme used to control the degree of superheat I  , Table 62. Parameters used to calculate saturation properties. Parameter R22 R134a Critical Pressure, kPa 4988.44 4056.32 Critical Temperature, K 369.28 374.18 al 7.1394518 7.7057291 a2 2.1352753 2.4186313 a3 1.7610879 2.1848312 a4 3.016996 3.4530733 n1 n2 1.5 1.5 n3 2 2 n4 4.25 4 (1) Outlet Ports from Compression Chamber/Inlet Ports to Expansion Chamber (2)Discharge Port for Compressor/Intake Port for Expander (3) Oring that separates low pressure/high pressure pockets in Compressor in the compression process (4) Oring that separates high pressure pockets before and after the exhaust port in the compression process (5) Suction Port for C ompre ssor/Di sch arge Port for Expander (6) Exhaust Port in compression process/ Inlet port in expansion process Figure 610. Flow path of refrigerant in both the compression and expansion processes Figure 611. Double acting, five vane modified automotive compressor Table 63. Machining modifications made to GAST NL32NCC1 to optimize geometric volume ratio Unmodified Modified S metric NonS mmtric Circular NonCircular Case 0 1 2 3 4 5 6 7 8 9 10 11 12 N, 4 a 8 8 8 8 8 8 8 8 8 8 8 8, deg 90 45 45 45 45 45 45 45 45 45 45 45 45 Inlet Start 55 55 55 55 55 55 .;11 I25 15 55 .;11 2 esn, deg 90 90 35 3 11 20 20 20 20 20 20 20 20 8ex, deg 235 235 2F 3 g i I 180 180 180 180 180 180 8 235 235 CutOff, V, 235 190 135 135 120 120 95 90 80 65 120 95 80 Exhaust, Vt 235 235 235 180 180 180 180 180 180 180 235 235 235 Relative to Rotor Center Displacements relative to Datum OOOO Fg re 2 n oiiemdfe ym ercadnny mti ocrua xade Aldmniosi nhs Pressure Regulator Multivane Expander Cooling Compressed Air P: Pressure transducer T: Thermocouple M: Massflow rate meter DLC: Dynamometer, Loadcell & Controller Valve Figure 613. Schematic of the experimental setup for compressed air and R22 tests with a rotaryvane expander CHAPTER 7 CONCLUSIONS AND RECO1V1VENDATIONS This chapter is a summary of the challenges, recommendations and conclusions of both the comprehensive modeling and experimental effort. The successful assessment of the performance of a twophase rotaryvane expander utilized in vapor compression refrigeration systems (VCRS) based on the results from extensive experimentation and a comprehensive componentlevel thermodynamic and fluid mechanic model has been made. Key technical challenges are realized from both primary (internal leakage, friction and throttling) loss mechanisms as well as those of secondary consequence (recompression, under or overexpansion, lubrication etc). Internal Leakage Losses Leakage losses from a maj ority of leakage paths cannot be necessarily neglected in twophase rotaryvane expanders. Unlike singlephase rotaryvane turbomachinery, significant variations in density and speed of sound, inherent with the vaporization of liquid, significantly alters the leakage flowrates. This due to a greater mass flux of two phase leakage in expanders when compared to conventional technology (i.e. compressors and airmotors) that results from the following: *Choking in leakage paths, i.e. maximum leakage flowrate, occurs at higher back pressures. Figure 71 illustrates the difference in the criticalpressure ratio required to realize choked flow for typical operating conditions in expanders and compressors, respectively. Both processes are isentropic. In the case of the expander, the fluid is initially a saturated liquid at the condensing temperature. The fluid then accelerates, necessitating the formation of vapor, and the velocity approaches that of the speed of sound if the back pressure is low enough. In the case of the compressor, the saturated vapor is assumed to undergo isentropic compression to the condensing temperature. The specific heat ratio is larger at higher condensing temperatures leading to a smaller criticalpressure ratio. It can be shown that for all practical purposes, the criticalpressure ratio for R22 vapor in the temperature range of OoC * Significant variation of the refrigerant' s density in the twophase region. Internal leakage has the greatest impact on a twophase rotaryvane expander' s performance during the charging and expansion processes. These are regions where the largest pressure differentials between cells exists (i.e. the driving potential) and also where the density of the refrigerant is significantly large. Although the speed of sound (or velocity if not choked) in a twophase medium is smaller than that of a vapor refrigerant, the discrepancy between the density has a much more dominant effect on the mass flowrate of leakage. * Gap sizes in conventional rotaryvane turbomachinery are extremely large. Larger gaps exist due to the significantly smaller density of the working fluid in the gaps between the moving parts in conventional rotaryvane machinery. These clearances must be reduced to within acceptable limits for the proper operation of a twophase device. Hence a special set of design criteria must be addressed. * Uncertainty in gap sizes. Uncertainties in regard to quantifying gap sizes are a significant obstacle to predicting the magnitude of leakage losses through all the leakage paths during operation. This can be attributed to bearing endplay which alters the clearances in two dimensions. Proper design of the bearing housing may influence this. The deformation of the endplates due to high pressure stresses will also alter clearances and may cause separation of boundarylayers and the transition to turbulence between the rotor and stationary endplates. * The leakage losses from the nonaxisymmetric flow in the axial gap between the rotor and endplates is most significant. The magnitude of leakage losses through this path during the intake and expansion processes has a significant impact on the efficiency of the expansion device. * Radial leakage through the minimum clearance between the stator and rotor cylinders greatly restricts the design and optimization of the intake angle spread and location. Depending on degree of subcooling, the density of the incoming fluid is substantially large. The magnitude of the leakage from this path depends on the spread and location of the intake port. The detrimental affect of reexpansion losses in compressors is significantly smaller than that of radial leakage in a twophase expander. A decrease in the number of vanes increases the contribution of leakage through the minimal radial gap between the rotor and stator cylinder. The increase of the number of vanes however increases the potential of internal leakage via other paths, increases frictional losses and decreases the mechanical strength of the rotor. Friction The curvature of the vanetip can severally impact the amount of leakage past the vanetips due to loss of contact with the statorcylinder. Even if no throttling is assumed in the intake port, there is a loss of contact with the statorcylinder through out the duration of the expansion process. The method used to provide continuous contact between the vanetips and statorcylinder is essential to optimum performance. A trade off exists between the throttling losses and increased frictional losses attributed to the method by which the incoming working fluid is introduced into the expander cavity. Vanes should be made out of highdensity materials that can erode and mold to the stator cylinder geometric curvature. This would eliminate the need for adequate undervane forces through intake ports or cumbersome, unreliable springs. Other Issues Depending on the flow conditions, throttling losses in twophase flow expanders are significantly larger than in singlephase flow expanders. It has been shown that the volumetric efficiency of a twophase rotaryvane expander is extremely sensitive to the design of the intake port. For a poorly designed intake port (low Cd), the volumetric efficiency is approximately 5060%. For a singlephase expander the volumetric efficiency is expected to be 7590%, due to the insignificant density variation that is inherent with the vaporization of liquid. A detailed intake model must be developed if two or more expander cells are in communication with the intake port. The throat that the expander cell makes with the intake port is expected to be the maj or flow restriction. Throttling losses in the exhaust port may be neglected when compared to the charging process since velocities associated with the discharge process are typically less and the flow area in the exhaust port is significantly larger. In vapor compression refrigeration technology the lubricant used is soluble and circulates freely within the system. A dedicated lubrication loop within a hermetic rotary vane expander may significantly reduce friction between sliding parts. The thin film of lubricant will also reduce gap sizes and alter internal leakage flows. The lubrication of the shaft bearings is accounted for by using sealed, prelubricated ball bearings. Leakage ratio, Expander sizing and Integration Concepts In order to harness the maximum amount of work output from an expander, different integration concepts must be evaluated according to operational speed requirements, ease of coupling and requirements related to capacity control and system performance. This task includes indepth offdesign calculations that result in significantly different inlet conditions and mass flowrates of the working fluid. An expander is sized so that the volumetric flowrate through the expander is equal to the volumetric flowrate of refrigerant at the condenser exit. * The amount of leakage is seen to increase due to a larger contribution from the leakage mass flowrate through the radial gap, minimum clearance, between the rotor and statorcylinder. Caution must be exercised when increasing the number of vanes due to possible increases in friction and decrease of mechanical strength of the rotor. * Sizing of the rotaryvane expander for twophase applications is critical with regard to determining the optimum operational speed to reduce the loss mechanisms presented above. * Inadequate sizing may lead to underexpansion. Depending on the order of magnitude of underexpansion, an economizer cycle may be a promising modification that would allow the use of two expansion devices in series with a separator between them. In this case there would be greater flexibility in the geometric design and operational speed of the expander. * Increase in rotational speed decreases internal leakage losses through the expander significantly. Extensive detailed modeling and experimentation is needed to determine the magnitude of detrimental effects such as friction and viscous drag. * The application of an expansion device in a refrigeration system should be primarily based on the system mass flowrate. For a given set of operational conditions, the cooling capacity will ultimately determine the geometric size of the expander, the degree of impact of the primary and secondary loss mechanisms and the rotational speed of the expander. *Once the rotational speed and the actual work output from the expansion device has been determined, the expander's shaft may be integrated in various configurations. The generated power from the expander can be: Coupled to the compressor on the same shaft. The matching of rotational speed and the complexity of a gearing system otherwise increase the complexity of this integration concept. Used to drive auxiliary equipment in the VCRS. This integration concept allows for the most flexible use of the power generated by the expander. The vapor compression refrigeration system has many components that require power such as fans, pumps, control devices etc. Used to drive external equipment. This is another flexible integration concept that allows equipment such as air compressors or standalone cycles to be driven by the expander. One promising alternative is to use the output power to drive a dedicated or integrated subcooling cycle. Figure 72 illustrates a typical expander sizing diagram. The diagram accounts for the nominal cooling capacity of the refrigeration unit, the displacement volume of an expansion device and the operational speed of that device for a given set of operational conditions. The two operating points detailed on the figure represent the current design point of a smaller deployable refrigeration unit and that of the minimum design condition. The current design point is that of a small expansion device operating at a low rotational speed due to the smaller cooling capacity of the unit. The minimum design point represents a design condition where the system mass flowrate is significantly larger than the leakage flowrate, the rotational speed of the expander is sufficiently large to reduce leakage losses and the geometric size of the expander is sufficiently large for reduced machining cost associated with less "strict" tolerances between the moving parts. Recommendations Great potential for use of a rotaryvane expander as a throttlevalve replacement has been presented analytically. The absence of complicated geometric profiles (e.g. screw, scroll) and complex valve timing and controls (e.g. reciprocating piston) make the rotaryvane expander a viable candidate. Valve timing is inherent through geometry and the principles of operation. This eliminates the need for complex models for valve dynamics and pulsation effects. Due to the aforementioned summary of technical challenges and limitations, the following can be recommended * Existing rotaryvane technology is limited by the aforementioned technical challenges and limitations which prevent a dropin vane expander from being developed as a retrofit. * Specialized design recommendations must be considered when reengineering current rotaryvane technology. * Systemoriented optimization that accounts for and overcomes the limitations alluded to in the set of comprehensive findings presented must be made. * The leakage losses from the nonaxisymmetric flow in the axial gap between the rotor and endplates is the most significant leakage path. The model developed is relatively ideal in its assumptions and doesn't take into account separated boundary layers, choking or turbulent fluid flow. A computational model must solve the compressible NavierStokes equations in order to do so. * Although there exists a tradeoff between reducing internal leakage losses and increasing frictional losses, internal leakage losses must be reduced in order to achieve suitable expander operation. This task should be given priority. As mentioned, internal leakage losses may be reduced by proper selection of design parameters and detailed engineering of tolerances and clearances. The use of a dedicated lubrication system may also significantly alter the characteristics of internal leakage. * Detailed analyses of the flow distribution within the complex geometry of two phase rotaryvane expanders must be carried using computational fluid dynamics. The solution of the compressible governing equations in this complex flow field will yield, among many others, the following Gradients of pressure and density with the expander cavity Prediction of viscous dissipation due to the formation of vortices during the charging and discharging processes A comprehensive account of all leakage potentials and phenomena The change of angular momentum caused by 'waterhammer like' phenomena during the charging process Accurate prediction of the volumetric efficiency by accounting for all throttling and cellinteraction effects in the intake port A detailed account of irreversibilities caused primarily by expansion waves generated due to underexpansion The existence of recompression of liquid which may be caused by various geometrical features The inception of cavitation due to the impinging of vapor bubbles on various surfaces Summary of Contributions * Comprehensive literature review of the application of expander technology in relevant thermodynamic cycles (First of its kind) * Comprehensive parametric systemlevel analysis and assessment of potentials and identification of key system design parameters * Developed comprehensive (scope and application) simulation model of twophase flow in a rotaryvane refrigerating expander * Identified and made quantitative analytical and experimental assessment of technical challenges and limitations that prevent a dropin vane expander from being developed as a retrofit. * Acceptable tolerances, geometry and operational parameters are identified. * Recommended specialized set of design criteria and identified systemoriented optimization guidelines Adequate sizing of both system/expander including integration concepts Reduction of internal leakage losses 0.86 0.8 0.74 0.68 0.62 0.56  Tw oPhase R22 a R22 Vapor Temperature, oC Figure 71. Variation of the criticalpressure ratio as a function of condensing temperature for a twophase expander and vapor compressor 45 Minimum Design 40 /1 Condition 35 1 Current Design 30 / / 25 /1 20 1,',c*  500 RPM 15 / 250 RPM 10 / 100 RPM 0 s 1000 RPM 0.E+00 5.E06 1.E05 2.E05 2.E05 3.E05 3.E05 yexp= 0.65 Displacement Volume, m3/rev Tcond=45C Te\a p =5 C Figure 72. Expander sizing diagram LIST OF REFERENCES Alphonso, J.Z., 2003. Proof of Concept of the lon Collider in Refrigeration Systems, M. S. Thesis. Department of Mechanical and Aerospace Engineering, University of Florida, Gainesville, FL. Badr, O., Naik, S., and O'Callaghan, P.W., 1991b. Expansion Machine for a Low Power Output Steam RankineCycle Engine. Applied Energy 39, 93116. Badr, O., Naik, S., O'Callaghan, P.W., and Probert, S.D., 1991a. Rotary Wankel Engines as Expansion Devices in Steam RankineCycle Engines. Applied Energy 39, 5976. Badr, O., Naik, S., O'Callaghan, P.W., and Probert, S.D., 1991c. Wankel Engines as Steam Expanders: Design Considerations. Applied Energy 40, 157170. Badr, O., O'Callaghan, P.W., and Probert, S.D., 1985a. MultiVane Expanders: Geometry and Kinematics. Applied Energy 19, 159182. Badr, O., O'Callaghan, P.W., and Probert, S.D., 1985b. MultiVane Expander Performance: Breathing Characteristics. Applied Energy 19, 241271. Badr, O., O'Callaghan, P.W., Hussein, M., and Probert, S.D., 1984. Multivane Expanders as Prime Movers for LowGrade Energy Organic RankineCycle Engines. Applied Energy 16, 129146. Badr, O., Probert, S.D, and O'Callaghan, P., 1985c. Multivane Expanders: Intemal Leakage Losses. Applied Energy 20, 146. Badr, O., Probert, S.D., and O'Callaghan, P., 1986a. MultiVane Expanders: Vane Dynamics and Friction Losses. Applied Energy 20, 253285. Badr, O., Probert, S.D., and O'Callaghan, P.W., 1986b. Influences of Vane Design and Lubricant on a Multivane Expander's Performance. Applied Energy 22, 271298. Bachr, H.D. and TillnerRoth, R., 1995. Thermodynamic Properties of Environmentally Acceptable Refrigerants Equations of State and Tables for Ammonia, R22, R 134a, R152a, and R123. SpringerVerlag. Baek, J., Groll, E.A., Lawless, P.B., 2005a. PistonCylinder Work Producing Expansion Device in a Transcritical Carbon Dioxide Cycle Part I: Experimental Investigation. International Journal of Refrigeration 28 (2), 141151. Baek, J., Groll, E.A., Lawless, P.B., 2005b. PistonCylinder Work Producing Expansion Device in a Transcritical Carbon Dioxide Cycle Part II: Theoretical Model. International Journal of Refrigeration 28 (2), 1 52164. Baek, J.S., Groll, E.A., and Lawless, P.B., 2002. Development of a Carbon Dioxide Based Field Deployable Environmental Control Unit to Replace HCFC22 or HFC 134A Units. Final Report submitted to the Air Force Research Laboratory, Report #16621. Baron, S. and Trembley, J., 2003. Cryogenic ReRefrigeration, Or How to Freeze Food More Economically Using Indirect Heat Exchange and TurboExpansion. In: Proceedings of the 21st International Congress of Refrigeration, Washington, D.C., USA, Paper No. ICRO267. Barszcz, Z., 1980. Dynamic Analysis of Pneumatic Vane Motors. Archiwumbudowy maszyn, Archive of Mechanical Engineering 27 (1), 2539. Beck, W.D., Stein, R.A., and Eibling, J.A., 1966. Design for Minimum Friction in RotaryVane Refrigeration Compressors. ASHRAE Transactions 72 (Part 1), No. 1974, 190197. Bein, M., Shavit, A and Solan, A., 1976. Nonaxisymmetric flow in the narrow gap between a rotating and a stationary disk. ASME Journal of Fluid Engineering, June, 217223. BenBassat, I., and Wolgemuth, C.H., 1972. Simulation of a Twostage Rotaryvane Steam expander. SAE No. 720737, September 1114, 1118. Bransford, E.O., and Stein, R.A., 1960. Design Control of Overcompression in Rotary Vane Compressors. Transactions of the ASME, Journal of Engineering Gas Turbines for Power, July, 221226. Brasz, J.J., 1995. Improving the Refrigeration Cycle with TurboExpander. In: Proceedings of the 19th Intemnational Congress of Refrigeration Vol. IIIa, The Hague, The Netherlands, August 2025, 246253. Brasz, J.J., Smith, I.K. and Stosic, N., 2000. Development of a Twin Screw Expressor as a Throttle Valve Replacement for WaterCooled Chillers. In: Proceedings of the 15th Intemnational Compressor Engineering Conference at Purdue Vol. 2, Purdue University, West Lafayette, INT, July 2528, 979986. Carey, V.P., 1992. LiquidVapor PhaseChange Phenomena: An Introduction to the Thermophysics of Vaporization and Condensation in Heat Transfer Equipment. Hemisphere Publishing. Cavallini A., 1996. Working Fluids for Mechanical Refrigeration. Presented at the 19th International Congress of Refrigeration, The Hague, August 1995, Review Paper, International Journal of Refrigeration 19 (8), 485496. Cerepnalkovski, I., 1991. Modem Refrigerating Machines. Elsevier Publishing Company. Chang, Y.S., Kim, M.S. and Ro, S.T., 2000. Performance and Heat Transfer Characteristics of Hydrocarbon Refrigerants in a Heat Pump System. International Journal of Refrigeration 23, 232242. Colbourne, D. and Suen, K.O., 2004a. Appraising the Flammability Hazards of Hydrocarbon Refrigerants Using Quantitative Risk Assessment Model Part I: Modeling Approach. International Journal of Refrigeration 27, 774783. Colbourne, D. and Suen, K.O., 2004b. Appraising the Flammability Hazards of Hydrocarbon Refrigerants Using Quantitative Risk Assessment Model Part II: Model Evaluation and Analysis. International Joumnal of Refrigeration 27, 784793. Collier, J.G., 1972. Convective Boiling and Condensation, McGraw Hill. Daily, J.W. and Nece, R.E., 1960. Chamber Dimension Effects on Induced Flow and Frictional Resistance of Enclosed Rotating Disks. ASME Joumnal of Basic Engineering, March, 217232. Darby, R., 2001. Chemical Engineering Fluid Mechanics, 2nd Edition. CRC Press. Disawas, S. and Wongwises, S., 2004. Experimental Investigation on the Performance of the Refrigeration Cycle using a TwoPhase Ejector as an Expansion Device. International Journal of Refrigeration 27, 587594. Dlugogorski, B.Z., Hichens, R.K. and Kennedy, E.M., 2002. Inert Hydrocarbonbased Refrigerants. Fire Safety Joumnal 37, 5365. Driver, R.W. and Davidson, D.P., 1999. Applications for the Hingevane Positive Displacement CompressorExpander. IMechE Conference on Compressors and their Systems, City University, London, England. Driver, R.W., 1996. A Rotary Positive Displacement Heat Pump Compressor and Turbine Combined in One Rotor. In: Proceedings of the 1996 International Compressor Conference at Purdue, July 2326, West Lafayette, IN. Edwards, T.C. and McDonald, A.T., 1972. Analysis of Mechanical Friction in Rotary Vane Machines. In: Proceedings of the Purdue Compressor Technology Conference, July 2527, 250262, West Lafayette, IN. Ertesvag, I.S., 2002. Analysis of the Vading ConceptA New RotaryPiston Compressor, Expander, and Engine Principle. In: Proceedings of IMechE Part A: Journal of Power and Energy 216 (3), 283290. Fartaj, A., Ting, D.S.K. and Yang, W.W., 2004. Second law Analysis of the Transcritical CO2 Refrigeration Cycle. Energy Conversion and Management 45, 22692281. Fischer, R.D., 1978. Feasibility Study and Hardware Design of a PivotingTip Rotary vane Compressor and Expander Applied to a SolarDriven Heat Pump. In: Proceedings of the 4th International Compressor Engineering Conference at Purdue, Purdue University, West Lafayette, IN, 233240. Fukuta, M., Yanagisawa, T. and Radermacher, R., 2003. Performance Prediction of Vane Type Expander for CO2 Cycle. In: Proceedings of the 21st Intemnational Congress of Refrigeration, Washington, D.C., USA, Paper No. ICRO251. Gnutek, Z. and Kalinowski, E., 1986. Use of a Rotary Blade Compressor and Expander in the Refrigeration Cycles. In: Proceedings of the 8th International Compressor Engineering Conference at Purdue Vol. 3, Purdue University, West Lafayette, IN, August 47, 10261034. Gnutek, Z., 1979. Mathematical Model of a Rotary Expander with Movable Rotor Blades. In: Proceedings of the XVth International Congress of Refrigeration, Volume I: Progress in Refrigeration Science and Technology, Venezia, Italy, 529 536. Granryd E., 2001. Hydrocarbons as Refrigerants An Overview. International Joumnal of Refrigeration 24, 1524. Hammad, M.A. and Alsaad, M.A., 1999. The Use of Hydrocarbon Mixtures as Refrigerants in Domestic Refrigerators. Applied Thermal Engineering 19, 1181 1189. Hays, L. and Brasz J.J., 2004. A Transcritical CO2 TurbineCompressor. In: Proceedings of the 17th Intemnational Compressor Engineering Conference at Purdue, Purdue University, West Lafayette, IN, July 1215, Paper C137, 17. Hays, L.G. and Brasz, J.J., 1996. TwoPhase Turbines for Compressor Energy Recovery. In: Proceedings of the 13th International Compressor Engineering Conference at Purdue Vol. 2, Purdue University, West Lafayette, IN, July 2326, 657662. Hays, L.G. and Brasz, J.J., 1998. TwoPhase flow Turbines as StandAlone Throttle Replacement Units in Large 20005000 Ton Centrifugal Chiller Installations. In: Proceedings of the 14th Intemnational Compressor Engineering Conference at Purdue, Purdue University, West Lafayette, IN, July 1417, 797802. Henderson, P.C., Hewitt, N. J. and Mongey, B., 2000. An Economic and Technical Case for a Compressor/Expander Unit for Heat Pumps. International Joumnal of Energy Research 24, 831842. Heyl, P. and Quack, H., 1999. Free Piston ExpanderCompressor for CO2Design, Applications and Results. In: Proceedings of the 20th International Congress of Refrigeration Vol. III, Sydney, Australia, Paper No. ICR05 16. Heyl, P., Kraus, W. E. and Quack, H., 1998. ExpanderCompressor for a More Efficient Use of CO2 aS Refrigerant. In: Proceedings of the '98 IIRGustay Lorentzen Conference on Natural Working Fluids, Oslo, Norway, 240248. Huff, H. and Radermacher, R., 2003. Experimental Investigation of a Scroll Expander in a Carbon Dioxide AirConditioning System. In: Proceedings of the 21st International Congress of Refrigeration, Washington, D.C., USA, Paper No. ICRO485. Huff, H., Lindsay, D. and Radermacher, R., 2002. Positive Displacement Compressor and Expander Simulation. In: Proceedings of the 16th International Compressor Engineering Conference at Purdue, Purdue University, West Lafayette, IN, July 16 19, 209215. Incropera, F. P. and Dewitt, D. P., 2002. Fundamentals of Heat and Mass Transfer, 5th Edition, John Wiley & Sons Inc. Jacazio, G., Piombo, B., Romiti, A. and Sola, A., 1979. The Optimization of the Performance of Vanetype Air Motors. In: Proceedings of the Fifth World Congress on Theory of Machines and Mechanisms, Montreal, Canada, July 813. Jung, D., Kim, C.B., Song, K. and Park, B., 2000. Testing of Propane/Isobutane Mixture in Domestic Refrigerators. International Joumnal of Refrigeration 23, 5 17527. Kauf, F., 1999. Determination of the Optimum High pressure for Transcritical CO2 Refrigeration Cycles. International Journal of Thermal Sciences 38, 325330. Kim, M.H, Pettersen, J. and Bullard, C.W., 2004. Fundamental Process and System Design Issues in CO2 Vapor Compression Systems. Progress in Energy and Combustion Science 30, 119174. Kim, Y.M., Shin, D.K., and Lee, J.H., 2004. A Scroll Expander with Heating Structure and their Systems. In: Proceedings of the 17th Intemnational Compressor Engineering Conference at Purdue, Purdue University, West Lafayette, IN, July 12 15, Paper CO24, 18. Kornhauser, A., 1990. The Use of an Ejector as a Refrigerant Expander. Preprints of the 1990 USNC/IIR Purdue Refrigeration Conference and the 1990 ASHRAEPurdue CFC Conference, Purdue University, West Lafayette, IN, July 1720, 1019. Lemmon, E.W., McLinden, M.O. and Huber, M.L., 2002. REFPROP: Reference Fluid Thermodynamic and Transport Properties. NIST Standard Reference Database 23, Version 7.0. Levy, S. 1999. TwoPhase Flow in Complex Systems, John Wiley & Sons. Li, D. and Groll, E.A., 2005. Transcritical CO2 Refrigeration Cycle with Ejector Expansion Device. International Journal of Refrigeration 27 (5), 766773. Li, D., Baek, J.S., Groll, E.A., and Lawless, P.B., 2000. Thermodynamic Analysis of Vortex Tube and Work Output Expansion Devices for the Transcritical Carbon Dioxide Cycle. In: Proceedings of the 4th IIRGustay Lorentzen Conference on Natural Working Fluids at Purdue, Purdue University, West Lafayette, IN, 433 440. Lorentzen, G. and Pettersen, J., 1993. A New, Efficient and Environmentally Benign System for Car Airconditioning. International Joumnal of Refrigeration 16 (1), 4 12. Lorentzen, G., 1994. The Revival of Carbon Dioxide as a Refrigerant. International Journal of Refrigeration 17 (5), 292301. Markoski, M., 2003. Improvement Possibilities of Vapor Compression Refrigerating Cycles by Utilization of Expansion Engines. In: Proceedings of the 21st International Congress of Refrigeration, Washington, D.C., USA, Paper No. ICR0006. Marsters, G.F., and Ogbuelfi, E., 1972. Rotaryvane Expander Development: Some Design Considerations. In: IECEC Conference Proceedings (729), 249254. Newton, A.B., 1972a. Controls for a MultiPhase Ejector Refrigeration System. US Patent Number 3,670,519, Assigned to BorgWarner Corporation, Chicago, IL. Newton, A.B., 1972b. Controls for a MultiPhase Ejector Refrigeration System. US Patent Number 3,701,264, Assigned to BorgWarner Corporation, Chicago, IL. Nickl, J., Will, G., Kraus, W.E. and Quack, 2003. Third Generation CO2 Expander. In: Proceedings of the 21st International Congress of Refrigeration, Washington, D.C., USA, Paper No. ICR0571. Nicktl, J., Will, G., Kraus, W.E., and Quack, H., 2002. Design Considerations for a Second Generation CO2 Expander. In: Proceedings of the 5h IIRGustay Lorentzen Conference on Natural Working Fluids at Guangzhou, China, 189196. Oosthuizen, P.H., and Carscallen, W.E., 1997. Compressible Fluid Flow, McGrawHill. Peterson, C.R. and McGahan, W.A., 1972. Thermodynamic and Aerodynamic Analysis Methods for Oil Flooded Sliding Vane Compressors. In: Proceedings of the Purdue Compressor Technology Conference, July 2527, 18. Preissner, M., 2001. Carbon Dioxide Vapor Compression Cycle Improvements with Focus on Scroll Expanders, Ph.D. Dissertation. University of Maryland, College Park, MD. Purkayastha, B. and Bansal, P.K., 1998. An Experimental Study on HC290 and a Commercial Liquefied Gas (LPG) Mix as Suitable Replacements for HCFC22. International Journal of Refrigeration 21 (1), 317. Robertson, G.F. and Wolgemuth, C.H., 1975. Analysis and Test Apparatus for a Vane Expander Using Steam. In: Proceedings of the Intersociety Energy Conversion Engineering Conference (IECEC), August 1822, Paper No. 759205, 14061410. Robertson, G.F. and Wolgemuth, C.H., 1978. Experimental and Analytical Study of Friction, Leakage and Heat Transfer in a Vane Expander. In: Proceedings of the Intersociety Energy Conversion Engineering Conference (IECEC), August 2025, Paper No. 789521, 14301441. Robinson, D.M. and Groll, E.A., 1998a. Efficiencies of Transcritical CO2 CyClCS with and without an Expansion Turbine. International Journal of Refrigeration 27 (7), 577589. Robinson, D.M. and Groll, E.A., 1998b. Heat Transfer Analysis of AirtoCarbon Dioxide TwoPhase Heat Absorption and Supercritical Heat Rej section. International Journal of Heating, Ventilating, AirConditioning and Refrigerating (HVAC&R) Research 4 (4), 327345. Schmidt, J. and Friedel, L., 1997. TwoPhase Pressure Drop Across Sudden Contractions in Duct Areas. International Joumnal of Multiphase Flow 23 (2), 283299. Sekhar, S.J., Lal, D.M. and Renganarayanan, S., 2004. Improved Energy Efficiency for CFC Domestic Refrigerators Retrofitted with Ozonefriendly HFC134a/HC Refrigerant Mixtures. International Joumnal of Thermal Sciences 43, 307314. Smith, I.K. and da Silva, R.P.M., 1994. Development of the Trilateral Flash Cycle System Part 2: Increasing Power Output with Working Fluid Mixtures. Proceedings of the Institution of Mechanical Engineers. Part A: Journal of Power and Energy 208, 135144. Smith, I.K. and da Silva, R.P.M., 1996. Development of the Trilateral Flash Cycle System Part 3: Increasing Power Output with Working Fluid Mixtures. Proceedings of the Institution of Mechanical Engineers. Part A: Journal of Power and Energy 210, 7593. Smith, I.K. and Stosic, N., 1995. The Expressor: An Efficiency Boost to Vapour Compression Systems By Power Recovery from the Throttling Process. Heat Pump and Refrigeration Systems Design, Analysis and Applications, presented at the 1995 ASME International Mechanical Engineering Congress, November 1215, AESVol. 34, 173181. Smith, I.K., 1993. Development of the Trilateral Flash Cycle System Part 1: Fundamental Considerations. Proceedings of the Institution of Mechanical Engineers. Part A: Journal of Power and Energy 207, 179194. Smith, I.K., Harrison, H.R. and Cox, M., 1990. A Preliminary Evaluation of the Groll Rotary Vane Compressor. In: Proceedings of the 1990 International Compressor Engineering Conference at Purdue, Vol. 1. Smith, I.K., Harrison, H.R., and Cox, M., 1992. Preliminary Evaluation of the Groll Rotary Vane Compressor. International Joumnal of Refrigeration 15 (2), 6973. Smith, I.K., Stosic, N. and Aldis, C.A., 1994. Lysholm Machines as TwoPhase Expanders. In: Proceedings of the 12th International Compressor Engineering Conference at Purdue, Vol. 1, Purdue University, West Lafayette, INT, July 1922, 6166. Smith, I.K., Stosic, N. and Kovacevic, A., 2001a. Twin Screw Machines to Replace Throttle Valves in Refrigeration Systems. Strojniski vestnik: Joumnal of Mechanical Engineering 47 (8), 484490. Smith, I.K., Stosic, N. and Kovacevic, A., 2001b. Power Recovery from Low Cost Two phase Expanders. Geothermal Research Council Annual Meeting, San Diego, CA. Smith, I.K., Stosic, N., Aldis, C.A. and Kovacevic, A., 1999. Twin Screw TwoPhase Expanders in Large Chiller Units. IMechE Intemnational Conference on Compressors and Their Systems, City University, London, England, September. Somayajulu, K.D.S.R., 1971. An Analysis of VaneinRotor Pump. Transactions of the ASME, Journal of Basic Engineering, December, 5055 17. Stoecker, W.F., 1998. Industrial Refrigeration Handbook, McGrawHill. Stosic, N., Smith, I.K. and Kovacevic, A., 2002. A Twin Screw Combined Compressor and Expander for CO2 Refrigeration Systems. In: Proceedings of the 16th International Compressor Engineering Conference at Purdue, Purdue University, West Lafayette, INT, July 1619, 703710. Tamura, I., Taniguchi, H., Sasaki, H., Yoshida, R., Sekiguchi, I., and Yokogawa, M., 1997. An Analytical Investigation of HighTemperature Heat Pump System with Screw Compressor and Screw Expander for Power Recovery. Energy Conversion and Management 38 (1013), 10071013. Taniguchi, H., Kudo, K., Giedt, W.H., Park, I. And Kumazawa, S., 1998. Analytical and Experimental Investigation of TwoPhase Flow Screw Expanders for Power Generation. Transactions of the ASME, Journal of Engineering for Gas Turbines and Power 110, October, 628635. Tashtoush, B., Tahat, M. and Shudeifat, M.A., 2002. Experimental Study of New Refrigerant Mixtures to Replace R12 in Domestic Refrigerators. Applied Thermal Engineering 22, 495506. Wolgemuth, C.H., and Olson, D.R., 1971. A Study of Breathing in Vane Type Expanders. IECEC Conference Proceedings, August 35, 2491258. Wongwises, S. and Chimres, N., 2005. Experimental Study of Hydrocarbon Mixtures to Replace HFC134a in a Domestic Refrigerator. Energy Conversion and Management 46, 85100. Yang, J.L., Ma, Y.T., Li, M.X. and Guan, H.Q., 2005. Exergy Analysis of Transcritical Carbon Dioxide Refrigeration Cycle with an Expander. Energy 30, 11621175. Zha, S., Ma, Y. and Sun, X., 2003. The Development of CO2 Expander in CO2 Transcritical Cycles. In: Proceedings of the 21st International Congress of Refrigeration, Washington, D.C., USA, Paper No. ICROO89. Zhang, H. and Yu, B., 1992. Future of the Refrigeration Cycle with Expander. In: Proceedings of the 11th International Compressor Engineering Conference at Purdue, Vol. 1, Purdue University, West Lafayette, INT, July 1417, 357363. Zoughaib, A. and Clodic, D., 2003. A TurboExpander Development for Domestic Refrigeration Appliances. In: Proceedings of the 21st International Congress of Refrigeration, Washington, D.C., USA, Paper No. ICR0 144. BIOGRAPHICAL SKETCH Ahmad M. Mahmoud was born February 14, 1979 in Kitchener, Ontario, Canada, where his father was a Ph.D. student in the Department of Mechanical Engineering at the University of Waterloo: the apple has clearly not fallen far from the tree! Shortly after his father' s graduation, Ahmad's family immigrated to the USA and Ahmad lived in Upstate New York and Connecticut, until the age of 13, where his father held faculty positions. In 1992, Ahmad's family moved to Kuwait where his father was hired as an associate professor of mechanical engineering. Ahmad attended the Universal American School until his high school graduation and then joined Kuwait University's Department of Mechanical Engineering as an undergraduate student in Fall of 1997. Ahmad ranked 2/150 in his graduating class. At Kuwait University, Ahmad also met his future wife, Ms. Iman AlNaggar, who was then a Molecular Biology undergraduate student at the same university. The two got engaged in their last year of undergraduate education and married upon graduation in June of 2002. A couple of months later, Ahmad and Iman both started graduate school at the University of Florida, where Iman also obtained her Ph.D. from the College of Medicine' s Interdisciplinary Program in Biomedical Sciences in Spring 2008. While at UF, Ahmad worked as a team leader at the Industrial Assessment Center during his Master' s graduate education and served as president of the Gainesville ASHRAE Chapter. Ahmad has also been active in a plethora of professional activities while in graduate school. Finally, Ahmad became a father when his daughter Salma was born on September 12, 2007. 267 PAGE 1 1 ANALYTICAL AND EXPERIMENTAL INVE STIGATION OF ROTARYVANE TWOPHASE EXPANDERS IN VAPOR COMPRE SSION REFRIGERATION SYSTEMS By AHMAD MOHAMED MAHMOUD A DISSERTATION PRESENTED TO THE GRADUATE SCHOOL OF THE UNIVERSITY OF FLOR IDA IN PARTIAL FULFILLMENT OF THE REQUIREMENTS FOR THE DEGREE OF DOCTOR OF PHILOSOPHY UNIVERSITY OF FLORIDA 2008 PAGE 2 2 2008 Ahmad Mohamed Mahmoud PAGE 3 3 I dedicate this work to God Almighty in partial fulfillment of His mandate to seek Knowledge: To my loving wife Iman, daughter Salma, fam ily and friends, without whose enduring patience and support this work would not have been possible. PAGE 4 4 ACKNOWLEDGMENTS I would like to begin by thanking God for giving me this great opportunity to learn and for putting in my path wonderful people who have he lped me and shown me the way. I want to thank all those people, and will try my best to remember them all here. I want to start by thanking my wife, Dr. Iman M. AlNaggar. To put it simply, this would not have been possible without her love support and daily dose of nagging! I would like to thank my parents, Dr. Moha med Abdelmoneim Mahmoud and Mrs. Faten Ismail Mahmoud for preparing me for and supporti ng me during graduate school. I also thank them for their unconditional love and endle ss prayers that have kept me on track. I would like to thank my mentors Dr. S. A. Sh erif and Dr. William E. Lear for their time, support, guidance and patience. Their technical a nd nontechnical mentorship drove me to excel at whatever I did, by following their example, and helped me become the researcher I am today. I am truly grateful. I would like to thank my committee members fo r their guidance and input: Dr. Gary Ihas, Dr. D. Yogi Goswami, and Dr. Skip Ingley. I have been fortunate to have a diverse, knowledgeable committee that had answers to my que stions, solutions to my problems, and great advice and encouragement. I would like to thank all the people in the Sherif and Lear Labs, especially Mr. Ayyoub Mehdizadeh, that have helped me throughout my y ears in graduate school, as well as make my long hours in the lab enjoyable. I would espe cially like to thank Mr. John Crittenden, engineering director at Triad Research Corporation Inc., fo r the guidance and knowledge he passed on to me regarding experimentation and solving countless techni cal challenges. I am honored to have worked with him. PAGE 5 5 I would also like to thank all the staff that ha s assisted me greatly at UF (Department of Aerospace and Mechanical Engineering). I would like to thank my friends who have made my years in Gainesville more enjoyable: Mr. Ibrahim Taman, Mr. Ahmed ElMahdawy, Mr. Ahmed ElHady ElMahdawy, Mr. Farouk Dey, Mr. Safwat Mohammad, Mr. Mahmoud Enani, Mr. Ramadan Ajredini Dr. Mujahid Abdulrahim and Dr. Fares AlBitar, to name a few. I would like to acknowledge the support from the Air Force Research Labs for partially funding my research and gradua te education: Dr. Aly Shaaba n, Dr. Ragab Moheisen and Mr. Reza Salavani. Finally, I would like to thank the University of Florida and the College of Engineering for providing such a rich and competitive graduate program in which I am very lucky to have been a part. PAGE 6 6 TABLE OF CONTENTS page ACKNOWLEDGMENTS...............................................................................................................4 LIST OF TABLES................................................................................................................. ..........9 LIST OF FIGURES................................................................................................................ .......10 NOMENCLATURE................................................................................................................... ...17 ABSTRACT....................................................................................................................... ............22 CHAPTER 1 INTRODUCTION AND OBJECTIVES................................................................................24 Introduction................................................................................................................... ..........24 Objectives..................................................................................................................... ..........24 2 LITERATURE REVIEW.......................................................................................................28 Expanders in Refrigeration and Heat Pump Systems.............................................................28 Conventional Heat Pump and Refrigeration Systems.....................................................29 Transcritical Carbon Dioxide Systems............................................................................37 Gas Refrigeration Cycles and Cryogenics.......................................................................44 Expander Selection............................................................................................................. ....45 3 PARAMETRIC ANALYSIS OF CYCLES...........................................................................46 Ideal Cycles................................................................................................................... .........46 Base Cycle..................................................................................................................... ..47 Economizer Cycle...........................................................................................................48 Internal Heat Exchanger (IHX) Cycle.............................................................................50 Actual Cycles.................................................................................................................. ........51 Effect of Subcooling on System Performance.................................................................52 Effect of Superheating on System Performance..............................................................53 Evaluation of CFC, HFC and Transcritical CO2 Refrigeration Cycles..................................54 Performance and Size Optimization of Compression Refrigeration Systems........................70 Pure Hydrocarbons as Refrigerants........................................................................................83 4 MATHEMATICAL MODEL OF AN IDEAL ROTARYVANE EXPANDER.................124 Literature Review of Modeling of Rotaryvane Expanders.................................................124 Model Development.............................................................................................................125 Thermophysical Model.........................................................................................................126 Geometric and Kinematic Model..........................................................................................126 PAGE 7 7Thermodynamic Model........................................................................................................128 Charging Process...........................................................................................................129 Expansion Process.........................................................................................................131 Exhaust process.............................................................................................................132 Ideal Expander Evaluation............................................................................................133 5 PRIMARY AND SECONDARY LOSS MECH ANISMS IN ROTARYVANE TWOPHASE REFRIGERATING EXPANDERS........................................................................154 Primary Loss Mechanisms....................................................................................................154 Internal Leakage Paths and Clearances................................................................................155 Types of TwoPhase Leakage Losses...................................................................................156 Axial Clearance Between Rotor and End Plates...........................................................161 Leakage around tips of vanes........................................................................................166 Leakage past the sides of the vanes...............................................................................167 Leakage between the faces of the vanes and the side walls of the rotors slots............168 Leakage in radial gap between the rotor and stator cylinder.........................................168 Friction Model................................................................................................................. .....169 TwoPhase Throttling Losses in the Inlet and Exhaust Ports...............................................180 Conventional Inlet to Expander Cavity.........................................................................184 Modified Inlet to Expander Cavity................................................................................187 Thermodynamic Model of the Actual Expansion Process...................................................188 Charging Process...........................................................................................................188 Expansion Process.........................................................................................................189 Exhaust process.............................................................................................................190 Expander Performance Evaluation.......................................................................................191 Performance Variation Due to StatorCylinder Geometry...................................................194 Heat Transfer.................................................................................................................. ......198 6 EXPERIMENTAL PROGRAM...........................................................................................214 Experimental Facility.......................................................................................................... ..214 Chilled Water/Heated Water Loop................................................................................214 Data Acquisition System...............................................................................................215 Unmodified Chiller Experimental Procedures......................................................................217 Dynamometer Selection, Data Acquis ition and RealTime Control Scheme.......................218 Rotaryvane Expander Selection..........................................................................................220 Modified Automotive Airconditioning Compressor....................................................220 Performance of Modified Compressor...................................................................221 Design Issues..........................................................................................................223 Designed and Machined Expander................................................................................223 Performance of Machined Expander......................................................................225 Modified AirMotor.......................................................................................................226 SinglePhase Experiments....................................................................................................229 Summary........................................................................................................................ .......231 7 CONCLUSIONS AND RECOMMENDATIONS...............................................................250 PAGE 8 8Internal Leakage Losses.......................................................................................................250 Friction....................................................................................................................... ...........251 Other Issues................................................................................................................... .......252 Leakage ratio, Expander sizing and Integration Concepts...................................................253 Recommendations................................................................................................................ .254 Summary of Contributions...................................................................................................256 LIST OF REFERENCES.............................................................................................................258 BIOGRAPHICAL SKETCH.......................................................................................................267 PAGE 9 9 LIST OF TABLES Table page 31 Summary of the percent changes in the system COP, refrigerating capacity and required work input by the addition of an expansion device for the ideal and actual R134a singlestage, economizer and IHX cycles.............................................................92 32 Percentage of cycle ir reversibility due to the various components in basic and modified R22, R134a and transcritical CO2 systems....................................................113 33 Hydrocarbons viewed as potential refrigerants...............................................................117 41 Summary of rota ryvane literature..................................................................................143 42 Geometrical input parameters..........................................................................................145 43 Typical operating conditions for a basic and modified 2 ton system..............................148 51 Primary leakage paths in a rotaryvane expander............................................................200 52 Governing equations and their discretized form describing onedimensional adiabatic Fannoflow from a reservoir............................................................................................201 53 Variation of operational and dimensionless parameters to model flow in axial gap as laminar and with a zerothorder approximation...............................................................202 54 Comparisons of contraction coeffici ents for turbulent singlephase flow.......................209 55 Variation of volumetric efficiency and fi nal pressure as a function on inlet angle in an expander with throttling losses accounted for.............................................................211 61 Experimental Therm odynamic State Points.....................................................................241 62 Parameters used to calc ulate saturation properties..........................................................244 63 Machining modifications made to GA ST NL32NCC1 to optimize geometric volume ratio................................................................................................................... ..247 PAGE 10 10 LIST OF FIGURES Figure page 31 A schematic of the ideal base cycle and the modified base cycle with an expansion device......................................................................................................................... ........86 32 Ts and Ph diagrams of the ideal ba se cycle and the modified base cycle with an expansion device............................................................................................................... .87 33 Ts and Ph diagrams of the econom izer cycle and an economizer cycle with an expansion device as a throttle valve replacement..............................................................88 34 A schematic of the economizer cycle and an economizer cycle with an expansion device as a throttle valve replacement...............................................................................89 35 A schematic of the IHX cycle and the modified IHX cycle with an expansion device as a throttle valve replacement ..........................................................................................90 36 Ts and Ph diagrams of the IHX cy cle and the modified IHX cycle with an expansion device as a throttle valve replacement..............................................................91 37 Variation of COP, between the modified cycle w ith an expansion device and the ideal cycle (R134a), with eva porating temperature for A) Tc=25oC, B) Tc=45oC for the base, economizer and IHX cycles................................................................................93 38 Variation of Qe and Wnet, between the ideal modified cycle with an expansion device and an ideal base cycle, with eva porating temperature for various condenser temperatures in a singlestage va porcompression refrigeration unit................................94 39 Variation of COP, between the modified cycle w ith an expansion device and the ideal cycle, as a function of the evapor ating temperature for both R22 and R134a for various expander efficiencies Tc=45oC........................................................................95 310 Variation of COP, between the modified cycle w ith an expansion device and the ideal cycle, as a function of the evapor ating temperature for various condenser temperatures for the actual and ideal cycl e configurations of the economizer cycle........96 311 Variation of COP, between the modified cycle w/ an expansion device and the ideal cycle, as a function of the evapora ting temperature for various condenser temperatures for the actual and ideal cy cle configurations of the IHX cycle....................97 312 Variation of refrigerating efficiency as a function of th e evaporating temperature for both the base (no expander) and ideal a nd actual modified cycle with and an expander at a condenser temperature of Tc=45oC..............................................................98 PAGE 11 11313 Variation of refrigeratin g efficiency as a function of the evaporating temperature for the actual base, IHX and economizer cycl es with an expander at a condenser temperature of Tc=25oC.....................................................................................................98 314 Variation of an ideal systems COP as a function of the degree of subcooling for various condensing temperatures.......................................................................................99 315 Variation of an ideal systems COP as a function of the degree of subcooling for various condenser temperatures and expansion processes...............................................100 316 Variation of the refrigerating effect as a function of the degree of subcooling for various condenser temperatures and expansion processes...............................................101 317 Variation in an ideal systems COP with respect to the evaporator temperature for different degrees of subcooli ng and expansion processes...............................................102 318 Variation of the difference in system COP,%, between the ideal cycle and modified cycle with an expansion device as a func tion of the evaporator temperature for various condenser temperatures and degrees of subcooling............................................103 319 Variation of the difference of the syst em COP, %, base cycle and modified cycle with an expansion device as a function of the degree of superheat in the evaporator for various condenser temperatures.................................................................................104 320 Variation of the refrigerating effect for an ideal cycle as a function of the degree of superheat for various condenser temperatures.................................................................105 321 Ts diagram of the basic system and th e modified system with an expansion device for a A) conventional refrigerati on system and B) transcritical CO2 refrigeration system......................................................................................................................... .....106 322 Variation of system coefficient of performance as a function of heat rejection pressure for various evaporating temperatur es for basic and modified transcritical CO2 systems.....................................................................................................................107 323 Percentage of cycle irreve rsibility associated with the heat rejection and expansion processes as a function of heat rejection pr essure for basic and modified transcritical CO2 systems.....................................................................................................................107 324 Coefficient of performance of basic and modified R22, R134a and transcritical CO2 systems as functions of the evaporating temperature......................................................108 325 Difference in coefficient of performan ce between basic and modified R22, R134a and transcritical CO2 systems as functions of th e evaporating temperature....................108 326 Difference in refrigerating effect between basic and modified R22, R134a and transcritical CO2 systems as functions of the evaporating temperature...........................109 PAGE 12 12327 Difference in system input work be tween basic and modified R22, R134a and transcritical CO2 systems as functions of the evaporating temperature...........................109 328 Volume ratio of the expander employed in modified R22, R134a and transcritical CO2 systems as functions of the evaporating temperature...............................................110 329 Difference in coefficient of performan ce between basic and modified R22, R134a and transcritical CO2 systems as functions of expander isentropic efficiency................110 330 Percentage of cycle irre versibility due to various components in a modified R22 system as functions of th e evaporating temperature........................................................111 331 Percentage of cycle irreve rsibility due to condensing pr ocess in basic and modified R22 and R134a systems as functions of the evaporating temperature..........................111 332 Percentage of cycle irreve rsibility due to the expansion process in basic and modified R22, R134a and transcritical CO2 systems as functions of the evaporating temperature.................................................................................................................... ..112 333 Dimensionless system irreversibility in basic and modi fied R22, R134a and transcritical CO2 systems as functions of the evaporating temperature...........................112 334 Variation of dimensionless COP, expa nder work output, expander volume ratio and condenser capacitance as a function of dimensionless refrigerating effect.....................113 335 Variation of dimensionless expander wo rk output and expander volume ratio as a function of evaporating temperature for various degrees of subcooling in the condenser...................................................................................................................... ...114 336 Variation of dimensionless condenser cap acitance as a function of evaporating temperature for various degrees of subcooling in the condenser.....................................114 337 Variation of dimensionless condenser capacitance as a function of degree of subcooling in the condenser for various values of condenser effectiveness....................115 338 Variation of dimensionless expander work output as a function of degree of subcooling in the condenser for various expander efficiencies.......................................115 339 Variation of dimensionless expander volume ratio as a f unction of degree of subcooling in the condenser for various expander efficiencies.......................................116 340 Variation of dimensionless COP as a function of degree of subcooling in the condenser for various expander efficiencies....................................................................116 341 Variation of dimensionless COP as a function of degree of subcooling in the condenser for various evaporator degree of superhea......................................................117 PAGE 13 13342 Variation of the refrigerating effect as a function of evaporating temperature for various refrigerants at a c ondensing temperature of A) 25oC and B) 45oC for the ideal base cycle............................................................................................................... .118 343 Variation of the ideal base cycle co efficient of performance as a function of evaporating temperature for various refriger ants at a condensing temperature of A) 25oC and B) 45oC.............................................................................................................119 344 Variation of compressor work as a func tion of the evaporating temperature at a condensing temperature of A) 25oC and B) 45oC for various refrigerants in an ideal base cycle..................................................................................................................... ....120 345 Variation of the increase of COP (when comparing the base cycle and the expander cycle) as a function of the evaporating te mperature for various refrigerants at a condensing temperature of A) 25oC and B) 45oC............................................................121 346 Variation of the decrease in network (when comparing the base cycle and the expander cycle) as a function of the evaporating temperatur e for various refrigerants at a condensing temperature of a) 25oC and b) 45oC.......................................................122 347 Variation of the increase in refrigerating effect (when comparing the base cycle and the expander cycle) as a function of the evaporating temperature for various refrigerants at a condens ing temperature of a) 25oC and b) 45oC....................................123 41 Flow diagram of the main computer program developed................................................142 42 Schematic of a generally oriented circ ular rotaryvane expander with 8 vanes described by two circular arcs..........................................................................................144 43 Variation of the inlet throat area with respect to angular displacement..........................146 44 Variation of the exit thro at area as a function of angular displacement for an 8vane circular MVE...................................................................................................................146 45 Pressure variation as a function of volume in an ideal expander for the cases of ideal, over and under expansion................................................................................................147 46 Variation of builtin volume ratio as a f unction of intake angle for different numbers of vanes....................................................................................................................... .....149 47 Variation of ideal volume as a functi on of angular displacement for different numbers of vanes.............................................................................................................149 48 Variation of ideal and actual volumes as a function of angular displacement.................150 49 Variation of pressure as a functi on of volume for various intake angles.........................150 410 Variation of pressure as a function of volume for different numbers of vanes...............151 PAGE 14 14411 Variation of mass within the expanders cell volume as a function of angular displacement for various intake angles............................................................................151 412 Variation of power as a function of a ngular displacement for different numbers of vanes.......................................................................................................................... ......152 413 Variation of power as a function of angul ar displacement for various intake angles......152 414 Variation of power as a function of volume....................................................................153 51 Schematic of nomenclature used and leakage paths of a circular rotaryvane expander with general orienta tion and a (a) conventional or (b) modified intake ports..199 52 Schematic of a typical leakage path.................................................................................200 53 Shear and pressure driven Couette flow..........................................................................201 54 Nonaxisymmetric pressure boundary condition on outer surface of the rotor...............202 55 Freebody diagram of a vane protruding outward from a ro tor slot at a local angle ....203 56 Schematic of generalized Couette flow in the axial gap between rotor and endplate....204 57 Variation of reaction forces on a vane w ith no vanetip curvature as a function of angular displacement.......................................................................................................204 58 Variation of reaction forces on a vane with a circular vane tip profile as a function of angular displacement.......................................................................................................205 59 Variation of leakage from/to the e xpander cavity as a f unction of angular displacement due to nonaxisymmetric flow between the rotor and stationary endplates for different intake angle spreads..........................................................................205 510 Variation of nonaxisymmetric leakage fr om/to the expander cavity for the ideal and throttling cases............................................................................................................... ..206 511 Variation of leakage from/to the expa nder cavity through the ga p between the sides of the vanes and endplates for different intake angle spreads........................................206 512 Variation of leakage to the expander cav ity from the rotor slot (modified intake) through the gap between the face of the vanes and rotor slot..........................................207 513 Variation of the ideal and actual mass flowrates through the expander as a function of rotational speed............................................................................................................207 514 Variation of the ideal and actual mass flowrates through the expander as a function of the number of vanes.....................................................................................................208 PAGE 15 15515 Comparison of way by which fluid is in troduced into the expanders cavity; A) conventional intake via intake port and B) modified intake vi a rotor slots through endplates to ensure vanetip and statorcylinder contact................................................208 516 Flow through a sudden contraction..................................................................................209 517 Schematic of the three phases of vane or ientation that occur during the intake process.210 518 Variation of pressure in expander cavity as a function of angular displacement for the ideal and actual (thr ottling only) cases............................................................................211 519 Schematic of the intake port of the m odified rotaryvane intake through the endplates and into the rotor cavity via rotor slots..................................................................212 520 Schematic of (a) symmetric (b) nonsymm etric noncircular rotaryvane expander comprised of four circular arcs (14) and a sealing arc (5)..............................................212 521 Variation of vane displacement as function of the leading vanes angular displacement for both a circul ar and noncircular MVE.................................................213 522 Variation of vane velocity as function of the leading vanes a ngular displacement for both a circular and noncircul ar rotaryvane expander....................................................213 61 The water heater used to add a constant heat load to the constant temperature water loop........................................................................................................................... .......236 62 Unmodified two ton aircooled barrel type water chiller.................................................236 63 Instrumentation map and schematic of the experimental setup for a vapor compression cycle with a bypass loop fo r rotaryvane expand er integration.................237 64 Variation of the measured pressure fo r the standard mode of operation in the unmodified chiller as a function of time..........................................................................238 65 Variation of the measured temperature for the standard mode of operation in the unmodified chiller as a function of time..........................................................................238 66 Variation of the measured pressure fo r the cutoff mode of operation in the unmodified chiller as a function of time..........................................................................239 67 Variation of the measured temperature for the cutoff mode of operation in the unmodified chiller as a function of time..........................................................................239 68 Variation of the compressor work for both the cutoff and standard modes of operation in the unmodified chi ller as a function of time................................................240 69 Schematic of the cutaway view of the bypass loop and evapor ator and the logic behind the continuous control scheme used to control the degree of superheat..............243 PAGE 16 16610 Flow path of refrigerant in both the compression and expansion processes....................245 611 Double acting, five vane modified automotive compressor............................................246 612 Unmodified, modified symmetric and nonsymmetric noncircular Expander (All dimensions in inches).......................................................................................................248 613 Schematic of the experimental setup for compressed air and R22 tests with a rotaryvane expander.......................................................................................................249 71 Variation of the criticalp ressure ratio as a function of condensing temperature for a twophase expander and vapor compressor.....................................................................257 72 Expander sizing diagram..................................................................................................257 PAGE 17 17 NOMENCLATURE 0 reference state, zerothorder 1 inlet state, location of minimum volume (i.e. cutoff) 2 location of maximum volume (i.e. at exhaust) A crosssectional area, m2 a speed of sound, m/s Acc( ) sliding acceleration of vane, m/s2 act actual Ak, Bk Fourier constants amb ambient b base cycle, boundary work, backpressure c Carnot calc calculated Cd discharge coefficient comp compressor cond condenser COP coefficient of performance, dimensionless CP critical point Cp specific heat at cons tant pressure, kJ/(kg.K) crit critical cv control volume (i.e. expander cavity) dt differential in time, s e eccentricity m, evaporat or, electric, exit state E total energy, kJ econ economizer cycle PAGE 18 18 ED expansion device Eu Euler number ex start of exhaust port exh exhaust exp expansion device f Darcy friction coefficient F force, N f saturated liquid, friction g saturated vapor, acceleration of gravity m/s2 gc gas cooler h specific enthalpy kJ/kg, evapor ator coolant, isenthalpic Hv height of vane, m i inlet, intermediate I specific irreversibility (kJ/kg), current (Amp) in inlet state, spread of intake port int intake L axial length of expander, m l leakage channel length, m leak corresponding to internal leakage Lv axial length of vane, m M Mach number m mass kg, mean m mass flowrate, kg/s max maximum MW molecular weight, kg/kmol PAGE 19 19 Nv number of vanes O center, location o original out outlet state P pressure, kPa p dimensionless pressure, exinexppppp q specific heat transfer, kJ/kg Q heat transfer rate, kW r dimensionless radial coordinate, /Rrrr r reservoir R rotor ref refrigerant, refrigerating Re 1 Reynolds number based on axial gap width RR rotor radius, mm RS( ) distance from statorcylinde rs center to periphery, m rv volume ratio (process or builtin) S gap aspect ratio, statorcylinder s specific entropy kJ/kgK, isentropic sc subcooling sf sliding friction sh superheat sys system T temperature K, torque Nm t time, s or minutes (unless otherwise noted) tv thickness of vane, m (=ts, slot thickness) PAGE 20 20 u specific internal ener gy kJ/kg, velocity m/s u dimensionless radial velocity, Ruur v dimensionless azimuthal velocity, Rvvr v throttling valve, vane, specific volume /kg m3 V voltage V, volume m3 vd viscous drag Vel( ) sliding velocity of vane, m/s w dimensionless axial velocity, 1/ww w specific work, kJ/kg W power, kW x quality, dimensionless X( ) vane height prot ruding from slot, m z dimensionless axial coordinate, 1/zz differential speed of angular rotation, RPM void fraction inner to outer radius ratio angle between successive vanes, degrees, leakage channel height, m 1 axial gap between rotor and endplate, m 2 radial gap between rotor and stator during sealing arc, m effectiveness, dimensionless efficiency leakage path flow coefficient dynamic viscosity, Pa.s PAGE 21 21 angular displacement/local angle, degrees cut angle at which expansion process begins, degrees ex spread of the expanders exhaust port, degrees in spread of the expanders intake port, degrees density, kg/m3 angular velocity, rad/s stream availability or exergy, angl e between base line and line through stator center from rotors center, degrees PAGE 22 22 Abstract of Dissertation Pres ented to the Graduate School of the University of Florida in Partial Fulfillment of the Requirements for the Degree of Doctor of Philosophy ANALYTICAL AND EXPERIMENTAL INVE STIGATION OF ROTARYVANE TWOPHASE EXPANDERS IN VAPOR COMP RESSION REFRIGERATION SYSTEMS By Ahmad Mohamed Mahmoud August 2008 Chair: S. A. Sherif Cochair: William E. Lear Major: Mechanical Engineering The refrigeration and aircondi tioning community has been searching for environmentally friendly refrigerants and ways to improve ener gy efficiency and to increase the potential for reductions in system size and weight for some time. These system improvements may manifest themselves in numerous ways but significantly impact terrestrial logistics differently. This study investigates the analytical and experimental util ization of rotaryvane ex panders as throttle valve replacements in vapor compressi on refrigeration systems with a specific application of these expanders in smaller deployable environmen tal control units. Th e findings support the conclusion that utilizing twophase expanders in refrigeration systems is very promising. Mathematical models for a systemlevel para metric cycle analysis were developed to assess potential gains in the cycle coefficient of performa nce for R22, R134 and transcritical CO2 vapor compression technology. Optimization st udies were conducted to determine the optimum performance of a refrigeration system s ubject to constraints of size and weight of both the condenser heat transfer area and the size and weight of the twophase expander. An exhaustive literature survey aids and va lidates the suitability of the type of positivedisplacement expander used, after which comprehensive component level thermodynamic and PAGE 23 23 fluid dynamic models of a rotaryvane expander we re developed to establish the performance of this expansion device as a function of design and fluid parameters. This included rigorous modeling of irreversible loss mechanisms such as throttling in the intake and exhaust ports, twophase internal leakage, fric tion, recompression, and under or overexpansion due to incorrect sizing of the expander or offdesign operation. Results from these models were used to esta blish the operating principles of a twophase rotaryvane expander. Experimental data gathered after modifying a conventional chiller with an alternative flow path, where a rotaryvane expander and dynamome ter have been installed, were used to improve the fidelity of the analytical mode l developed. Issues such as realtime control to satisfy systemlevel constraint s, expander sizing and operational speed and inadequate operation were addressed. The analytical model develope d along with singlephase experimentation were used to understand and overcome componentlev el complications and inadequacies due to irreversible effects. PAGE 24 24 CHAPTER 1 INTRODUCTION AND OBJECTIVES Introduction The refrigeration and aircondi tioning community has been searching for environmentally friendly refrigerants and ways to improve ener gy efficiency and to increase the potential for reductions in system size and weight for so me time. Cycle improvements may manifest themselves in many ways such as using multista ge compression with intercooling and/or flash gas removal as a means to reduce the work input to the compressor, employing economizers and/or employing expansion devices to recover work. There are two advantages to using expansion de vices with output wor k. The first is that lower enthalpy refrigerant is obtained at the in let of the evaporator and hence increases the refrigerating effect of the evapor ator. The second is the extra work that can be extracted from the expansion process, which can then be used to lower the input requirement of the compressor or to operate auxiliary machinery such as fans or pumps. Both effects serve to increase the coefficient of performance (COP) and hence raise the energy efficiency of the system as well as increase the potential for reducti ons in system size and weight. Objectives The proposed overall approach is to comb ine experimentation with thermodynamic and fluid dynamic modeling in order to demonstrat e the operating principles, to discover any unanticipated difficulties, and to establish a qualified design code which may subsequently be used for optimizing airconditioning and refrigeration systems for a wide range of applications. A detailed list of these objectives is as follows: Conduct a literature surv ey of work on the use of various expansion devices in relevant engineering cycles. This exhaus tive survey would aid and validate the suitability of the selected type of positivedisplacement expander used. PAGE 25 25 Perform systemlevel parametric analysis of vaporcompression refrigeration systems to assess potential gains in the cycle COP. This includes examining the factors that affect reduced power requirements and in creased refrigerating capacity. Develop a thermodynamic and fluid mechanic componentlevel model of twophase rotaryvane expanders to establish their e fficiency as a function of design and fluid parameters. Develop a comprehensive model of primary irreve rsible effects such as internal leakage, friction, and throttling within the twophase expander and present relevant discussion or models of secondary losses. Design, build and modify an experimental refrig eration system to incorporate a rotaryvane expander based on model inputs including rota ryvane expander sizing and rotational speed. Develop an appropriate realt ime control scheme to mimic the operational function of conventional thermostatic expansion valves, i.e. to regulate mass flowrate through the rotaryvane expander, to satisfy systemlevel constraints. Utilize the developed computer program and comprehensive singlephase experimentation to understand, recommend and possibly overc ome componentlevel complications and inadequacies due to irreversible effects. Utilize the experimental results where necessary to improve the fidelity of the qualified design code. Based on the motivation behind and objectives of this investigation, a detailed review of recent literature pertaining to the use of expanders as throttle valve replac ements in refrigeration units was conducted. The review en tails the use of twophase e xpanders in conventional vapor compression refrigeration systems with conventi onal CFC, HCFC and HFC refrigerants as the working fluids. The review also encompasses th e use of twophase expanders in geothermal systems and transcritical carbondi oxide refrigeration cycles as well as singlephase expanders utilized in organic Rankine power cycles and gas refrigeration cycles. This section will enable the reader to understand the f undamentals of this technology as well as highlight practical issues/problems that may have been presented by various researchers in th is regard. The type of expander used was chosen and suitability was based on this e xhaustive review. PAGE 26 26 Analytic parametric modeling of the ideal a nd actual vapor compressi on refrigeration cycle and modified cycles such as the vapor compre ssion cycle with an expander, a liquidtosuction heat exchanger and a multistage vapor compression cycle with an economizer was then conducted. These cycles have been analyzed in bot h ideal and actual cases and have also been analyzed with the additional modification of uti lizing a twophase expande r as a throttle valve replacement. The working fluids investigat ed in this study incl ude: R12, R22, R134a, pure hydrocarbons and transcritical carbondioxide. Optimization studi es were also conducted to determine the optimum performance of a refriger ating unit subject to c onstraints of size and weight of both the heat transfer ar ea and the size and weight of the tw ophase expander. The development of a detailed thermodynamic and fluid dynamic model of the rotaryvane expander followed. The geometry, kinematics a nd thermodynamics of a circular rotaryvane expander were described mathematically to dete rmine its ideal performa nce as a function of design and fluid parameters. A robust thermodynamic model that takes into account primary loss mechanisms such as friction and internal leak age and presents a disc ussion, models when necessary, of secondary irreversib le effects such as throttling in the intake and exhaust ports, twophase internal leakage, friction, rec ompression and under or overexpansion due to incorrect sizing of the expande r is then described. An experimental program that has been develo ped at the University of Florida for testing the use of a twophase rotaryv ane expander in a refrigeration unit is then detailed. The equipment and instrumentation used in the lab to gather experimental data to validate and improve the fidelity of the analytical models are described. The sizing and selection of the rotaryvane expander and the dynamo meter is presented. Finally the means of realtime control of the expander via a highspeed programmab le dynamometer controller is presented. The PAGE 27 27 developed computer program and comprehensiv e singlephase experimentation was used to understand, recommend and possibly overcom e componentlevel complications and inadequacies due to irreversible effects such as friction and internal leakage. A summary of key technical challenges, recomme ndations and conclusions from both the comprehensive modeling and experimental effort is then presented. PAGE 28 28 CHAPTER 2 LITERATURE REVIEW The concept of utilizing expansion devices in various thermodynamic cycles is one that has been described in scattered tech nical literature. Example applicat ions in which expanders have been used to recover and utilize lost work or waste heat include geothermal applications, Organic Rankine Cycles (ORC), and refrig eration cycles. A thorough understa nding of these applications along with the types of working fluids used, the types of expansion devi ces used and inherent loss mechanisms within those expansion devi ces will allow further advancement of such concepts. In literature dealing with expansion devices, the working fluid has been predominantly air, steam, refrigerant vapor or tran scritical carbondioxide. In the present study, expansion takes place in a refrigerants twopha se region where additional comp lexities (e.g. erosion due to cavitation and increased internal leakage due to significant density variation) arise. Although complexities exist with the expansion of gases, vapors, and transcritical fluids, the loss mechanisms of internal leakage, friction, and heat transfer and how they affect overall performance of different types of expanders ar e qualitatively comparable to one another. Understanding and incorporating these effects will aid in developing a mathematical model of a twophase expander employed in a vapor comp ression refrigeration/ heat pump system. Expanders in Refrigeration and Heat Pump Systems There has been much effort to quantify th e amount of savings and the methods by which the work recovered and additional refrigerating effect could be utilized from the use of expanders in refrigeration and heat pump systems. Among the res earchers who investigat ed this are Zhang and Yu (1992), Markoski (2003) and Brasz (1995). PAGE 29 29 Zhang and Yu (1992) compared ideal and m odified refrigeration cycles for R12, R22, R502 and R707. They found savings from utilizing twophase expanders and recommended the use of expanders. They failed to elaborate on the complexities associated with utilizing expanders in the twophase region. They men tion only that components of the expander are small and hence friction losses are large and that problems may arise from lubrication related issues. Brasz (1995) introduced the use of a turboe xpander in large (>85 tons) vaporcompression refrigeration systems utilizing R134a as the working fluid. According to Brasz, a turbine efficiency of 39% could overcom e the disadvantages of using R134a instead of lowpressure R11 or R123 refrigerants. He c oncluded that the application of this technology is applicable where the expander rotational speed matche s that of an existing drive train. Markoski (2003) presented thre e alternative methods by which the expansion work from an expansion engine can be utilized in a va por compression refrigera tion cycle. The author provides brief guidelines and analyses for the use of the power recovered by the expander in conventional and nonconventional vapor compressi on cycles as well as powering a circulation pump for liquid circulation through a flooded evaporator. Conventional Heat Pump and Refrigeration Systems The use of expansion devices in conventiona l vaporcompression refr igeration cycles has been investigated by Hays and Brasz (1996, 1998), Smith and Stosic (1995), Zoughaib and Clodic (2003), Smith et al. (1994, 1996, 1999, 2001a 2001b), Brasz et al. (2000), Kornhauser (1990), Fischer (1978), Kim et al. (2004), Tamura et al. (1997), Disawas and Wongwises (2004), Henderson et al. (2000) and Ta niguchi et al. (1983). In most of the aforementioned studies, unless mentioned otherwise, a throttling valve was used as the default control mechanism responsible for ensuring the degree of superheat of the PAGE 30 30 refrigerant leaving the evaporator. The use of a throttling valve would however cause a loss in the available pressure difference that may be utilized in an expansion device for work recovery. Tamura et al. (1997) investigated the use of a screw expander in a high temperature (up to 180oC) binary heat pump with steamwater and ammonia as the working fluids. They found a COP improvement of about 40% when compar ing a hightemperature heat pump with one employing an isentropic screw expander and one without in the ope rating range of 40180oC. Fisher (1978) described the concept of a pi votingtip rotaryvane compressor and expander applied to a solarpowered vapor compression heat pump. The solar heat pump had a capacity of 3 tons and R12 was selected since the author found that the required compressor and expander displacements are of reasonable size to provide good efficiencies and lo w manufacturing costs. Compression and expansion characteristics were ta ken into consideration before selecting the working fluid as to avoid entirely the complex ities that arise when expanding into the twophase regime. The author also describes the performa nce of pivotingtip gas bearings, which were utilized to reduce vanetip friction in rotaryv ane turbomachinery. Estimated efficiencies of 85% were assumed for both the compressor and expande r to reflect improvements that the pivotingtip gas bearings will introduce. A cooling coeffici ent of performance of 0.56 at design conditions was achieved. Taniguchi et al. (1983) presented a detailed an alytical and experiment al investigation of helical screw twophase expanders in large refrigeration system s whose working fluid is R12. They stated the added advantage of utilizing positive displacement turbomachinery as twophase expanders because they operate without erosion a nd slip losses between liquid and vapor phases. The authors investigated the de gree of subcooling on the performance characteristics of this modified vapor compression cycle. Effects of va por formation during the expansion process as PAGE 31 31 well as internal leakage losses were accounted fo r in the theoretical model. The helical screw expander used in this study ha d a builtin volume ratio of 5:1. The expansion process volume ratio of R12, at the operating conditions, however depended on the degree of subcooling in the condenser and varied from 13.2:1 and 10.6:1 corresponding to 0 and 12 K of subcooling respectively. The authors concluded that the isen tropic efficiency of the expander increased from 30 to 60% at rotational speeds of 500 and 3000 rpm respectively. Th e authors predicted analytically an isentropic efficiency a pproaching 80% for larger screw expanders. Kornhauser (1990) analytically investigated the use of a twophase ejector as a refrigerant expander to replace the throttli ng process in a vaporcompressi on refrigeration system. The author cites other expansion devices as expens ive and susceptible to damage because of twophase flow. The power that is r ecovered by the expander is not ex tracted or coupled in any way but is used to partially comp ress the refrigerant leaving the evaporator. The effects of both isentropic expansion and part ial compression significantly increase the coefficient of performance of the system. The system is sim ilar to a twostage refrigeration unit where the work extracted from the high pressure stage is used to drive the compre ssion process of the low pressure stage. A throttling valve expands the refrigerant in the low pressure cycle to the evaporator pressure. According to the author this expansion is across a small pressure difference and is negligible when accounting for the maximu m work extraction from the cycle. Theoretical calculations were made to compare the conventiona l and ejector refrigeration cycles. A constant pressure mixing model of the ejector was use d. The author found that for an ideal ejector expansion cycle, an increase in the cycle coe fficient of performance of 13%, 21%, 20%, 17%, and 30% would be realized for R11, R12, R22, R113 and R502 respectively. Results PAGE 32 32 detailing the decrease in compressor displa cement and the performance gains of R114, R500 and R717 are also presented. An interesting obstacle that Kornhauser ( 1990) eludes to is the fact the conventional expansion valve would defeat any performance improvements made by the use of an expansion device. According to Kornhaus er (1990), Newton (1972a, 1972b) has patented two methods by which the liquid flow through the expander may be controlled. Controlling the mass flowrate through the ejector may be accomplished by controll ing the specific volume of the entering fluid by means of injecting small amounts of hot gas into the refrigerant exiting the condenser. Varying the nozzle area could also control the mass flowrate through the ejector. Disawas and Wongwises (2004) experimentally investigated the use of a twophase ejectorexpansion device in a conventional vapor compression refrigeration system whose working fluid is R134a. They used an ejector as the sole method by which expansion occurs unlike other investigators who used a throttli ng device. They reported a maximum increase in COP of 2% and 10% at an ev aporating temperature of 16oC and a condensing temperature of 37 and 32oC, respectively. This is not an evapora ting temperature typica l in airconditioning applications. The ejector system performance, when compared to the conventional system, decreases greatly as the condensi ng temperature is increased and the evaporator temperature is decreased. Hays and Brasz (1996) presented a theoretical investigation of the power recovered by the use of a twophase turbine in a refrigeration system with R134a, R22, R123 and propane as the working fluids. The calculations were run assuming the turbine had isentropic efficiencies of 55 and 70%. The authors also experimentally investig ated the performance of twophase turbine in a PAGE 33 33 500 ton R134a chiller. The authors determined a turbine efficiency of 6065% and discussed the turbine rotor loss mechanisms that accounted for this deficiency. Hays and Brasz (1998) report on the implemen tation of a standalone turboexpander as throttle valve replacement for a large 20005000 ton centrifugal chiller installation at a commercial building in Manhattan, New York. They reported that over 70 refrigeration units employing twophase turbines are in operation in a wide range of industrial and commercial applications. They concluded that at an evaporator temperature of 44oF (6.7oC) and a condensing temperature of 86oF (30oC), 15 and 180 kW of power can be produced by a 500 and 6000 ton chiller unit respectively. These values are ideal a nd do not take into consideration the generator efficiency. The installation cost for one of these large units is approximately $1000/kWe initially and should decrease to a minimum of $400/kWe for additional units. Zoughaib and Clodic (2003) inves tigated the use of a microtu rbine as an expansion device in a domestic refrigeration unit. The power recove ry would then be used to drive an auxiliary fan(s) that would, through forced convection, ensure that no frost would form on the heat exchanger of nofrost domestic appliances. The aut hors parametrically investigated the effect of subcooling on the modified refrigeration cycle. Th e authors assumed a micr oturbine isentropic efficiency of 80% and hence concluded that a 1.1% increase in the coefficient of performance and 1.12 W of generated pow er were realized. Smith et al. (1994) investigated the therm odynamic modeling of a Lysholm machine as a twophase expander in larges cale refrigeration systems utilizing R113 as the working fluid. They discussed the differences that existe d between their model and the one proposed by Taniguchi et al. (1983). Among the differences that the authors pointed out was the fact that Taniguchi et al. (1983) assumed that the filling process would take place at a constant pressure. PAGE 34 34 According to the authors, the filling process does not take place at a constant pressure because the acceleration of the entering re frigerant causes a pressure drop, which in turn induces flashing and thus causes higher fluid velocities. The authors estimated that isentropic efficiencies of about 7080% could be expected. Smith and Stosic (1995) descri be the principle behind a novel machine, which they dubbed the expressor that is comprised of a coupled twinscrew compressor and twinscrew expander in a single casing. They investigated the use of this expressor unit as a throttle valve replacement in a conventional large chiller where R134a is the working fluid. The authors estimated the expander adiabatic efficiency as 70% and explaine d that large leakage losses do not affect the performance of the expander because they are in the direction of the bulk flow. A coefficient of performance gain of approximate ly 10% and 7.5% with 0 and 5oC subcooling respectively was realized. A throttle valve is di rectly upstream of the expressor device. Brasz et al. (2000) discuss the disadvantages of this mechanism that make th is technology rather e xpensive to implement. The primary disadvantages mentioned were the need for a timing gear, the high cost of seals and the need for two sets of rotors to carry out the compression and expansion processes. Smith et al. (1996) presented the high effici ency design of twophase screw expanders in various cycles. Smith (1993) first presented the use of these twophase expanders in a trilateral flash cycle (TFC). In this cycle a fluid is pressuri zed adiabatically, heated at constant pressure to its boiling point, expanded adiabatically as a tw ophase mixture and then condensed at constant pressure. Smith et al. (1994) then investigated the us e of different working fluid mixtures to increase the power outpu t of a twophase expander employed in the TFC. Smith et al. (1996) concluded that if a small amount of undere xpansion is permitted, high speed, low builtin volume ratio designs, with roughly half the vol umetric capacity required for lower speed full PAGE 35 35 expansion alternatives, attain the highest overall adiabatic efficienci es. They also reported that from a large airconditioning unit data they we re able to predict a 710% increase in the coefficient of performance of the system. This could be achieved by ut ilizing the twophase screw expander to drive a compressor in a herm etic unit called the expressor, (see Smith and Stosic 1995) with an adiabatic efficiency of approximately 70%. Smith et al. (1999) investigated the feasibility of utilizing a twin screw twophase expander in a large (500 ton) chill er unit that operated with R134a as the working fluid. They attained an expander adiabatic efficiency of approximately 70% They listed the most significant factors that hinder the adoption of twophase ex pander in refrigeration systems as poor adiabatic efficiencies and high cost of construction and installation. They discussed the results found by Smith et al. (1996) as to the improper selecti on of the builtin volume of the expander when compared to the actual expansion process volume ratio. Brasz et al. (2000) presented the development of a twin screw expr essor with only one pair of rotors as a throttle valve replacement for a large wate rcooled chiller. The need for a timing gear and high cost seals was avoided by the use of high profile rotors developed earlier by the authors. The compression process in the e xpressor unit recompresse s the vapor that is generated in the expansion pro cess by means of power that is recovered. The recompressed vapor would then be piped directly to the conde nser inlet. The authors discussed the pros and cons of different methods by which the power rec overed may be utilized. They indicated that the efficiency of the expandercompressor mechanis m, expander and compressor is approximately 55%, 70% and 80% respectively. At part load, the speed reducti on caused by the reduced flow via the throttling valve negates th e use of a control system. Initia lly the builtin volume ratio of the screw expander was designed and built at 2.85:1. The authors found however evidence of PAGE 36 36 overexpansion when this 2.85:1 expander was us ed with R134a and R113 whose expansion process volume ratios were 11.4:1 and 12.9:1 re spectively. The authors then progressively reduced the builtin volume ratio of the expander to 1.85:1 to a void overexpansion. Smith et al. (2001a) investigated the use of a helical twin screw compressorexpander as a replacement to the throttle valve in a refrigeratio n system. Poor adiabatic efficiencies as well as high manufacturing and installation costs are amo ngst the most significant factors hindering the extensive use of twophase expanders. According to Smith et al. (2001a) they have shown that the adiabatic efficiency of the expander, a reported maximum of 70%, is significantly higher because the builtin volume ratio of the expander is less than the volume ratio of the actual expansion process. They designed, built and tested an expander unit with a builtin expansion ratio of 2.85:1. The expander provided a 3.610.3% increase in the syst em coefficient of performance for an actual expansi on process volume ratio of 11.4:1. Smith et al. (2001b) presented an economical analysis of twophase screw expanders that may be utilized in organic Rankine cycles, Trilateral Flash Cycles and refrigeration units. They reported a peak adiabatic efficiency of 76% Although this technology could be utilized in refrigeration systems, the authors conclude that it would be more signifi cant for Trilateral Flash Cycles (Smith, 1993 and Smith et al., 1994, 1996) Kim et al. (2004) presented preliminary results of an investigation of the use of a scroll expander with a heating structur e and a proposal of their use in a refrigeration cycles as twophase expanders. When used in hightemperature and highpressure applications, clearances in both the radial and axial direc tions are caused by differential th ermal expansion of the scroll elements. This may result in a decrease in th e expander efficiency as well as the expanders specific power output. The authors investigated the use of a heat pipe that would provide a PAGE 37 37 uniform temperature throughout the scroll elemen ts by means of heating. According to the authors, if the scroll expander w ith a heating structure is used in twophase expansion, instances of over expansion will cause the liquid in the expander to evapor ate by means of heat from the refrigerated space. They concluded that this in turn would both increase the power output of the expander and the cooling capacity of the system due to a higher volumetric expansion ratio needed in the expander. In this case the e xpander could also be t hought of as a partial evaporator. Henderson et al. (2000) theore tically investigated the ec onomics of employing compressorexpander devices in heat pumps th at use R410 as their working fl uid. They investigated using a screw compressorexpander since it was found th at the rotaryvane compressorexpander would likely fail because of excessive friction at the vanetip/stator surface a nd could also be very noisy. They found that if the device had an 80% isentropic efficiency, the system COP would increase by 30%. They have not specified the oper ating conditions or any component efficiencies in their study. In a majority of the studies, no subcooling in the condenser was allo wed as to determine the maximum possible work extraction from the expansion process. This however would result in immediate formation of vapor upon the slightest decrease in pressure and increase of velocity. This in turn could cause cavita tional erosion, especially in dy namic expansion devices. This phenomenon however has not been addressed directly. Transcritical Carbon Dioxide Systems The inherent coefficient of pe rformance of a transcritical CO2 cycle is less than the coefficient of performance of a conventiona l vapor compression cycle. Among the methods by which this deficiency may be overcome is to utilize expanders as throttle valve replacements. One primary difference between the use of expanders in a transcritical CO2 cycle and a PAGE 38 38 conventional cycle is the fact that complexities such as cavitation on ly take course as the velocity of the incoming refrigerant has decreased (i.e. at later stages in the expansion process). In conventional vaporcompression cycles these co mplexities may occur immediately and is a strong function of the degree of s ubcooling and the severity of lo ss mechanisms during the intake phase of the expansion process. The use of e xpanders in transcritical carbon dioxide systems have been investigated by Robinson and Gr oll (1998a, 1998b), Baek et al. (2005a, 2005b), Li and Groll (2005), Huff et al. (2002, 2003), Fukuta et al. (2003), Zha et al. (2003), Nickl et al. (2002, 2003), Stosic et al. (2002), Hays and Brasz (2004), Heyl and Quack (1999), Li et. al (2000), Driver (1996), Driver and Davidson (1999), Heyl et al. (1998), Ertesvag (2002) and Preissner (2001). Robinson and Groll (1998a, 1998b) analyti cally investigated and compared the performance of a transcritical CO2 cycle and a conven tional R22 refrigeration cycle with and without an expansion turbine. They found that use of an internal heat exchanger along with an expansion device decreased the COP of the transcritical CO2 cycle by 68%. They concluded that the stream availability following the heat rejecti on process in the condenser is better utilized by an expansion device rather than an internal he at exchanger. They also found a 23% COP increase when comparing an R22 refriger ation cycle and a transcritical CO2 cycle both with expansion devices with a 60% isentropic efficiency ope rated at an evaporating temperature of 5oC and a condensing temperature of 35oC. Baek et al. (2005a, 2005b) studied both analytic ally and experimentally the effect of the addition of a newly designed pistoncylinde r workproducing device to a transcritical CO2 cycle. Experimentally they found a 10% increase of the cycle COP taking into account both the increase in evaporator capacity and expansion work. The limiti ng factor in this study was the PAGE 39 39 isentropic efficiency of the expander, which wa s reported to be 10% (experimentally) and 34% (theoretically). The discrepancy between the two can be attributed to the 30% uncertainty in the instruments used for measurements as well as th e inadequate theoretical internal leakage model that was used. Li and Groll (2005) analytically investigated the use of an ejectorexpansion device in a transcritical CO2 cycle. They found that the cycle CO P can be increased by 16% by assuming that the ejector has an isentropic efficiency of 90%. They have however not investigated the potential loss in efficiency due to various loss mechanisms. Heyl and Quack (1999) presented the process calculations, design and results of a novel free piston expandercompressor for a CO2 cycle. The expandercompressor device had two expansion and two compression cylinders and was a ssumed to have an isentropic efficiency of 85%. They noted an increase of cycle efficien cy of 38.7% and 10% w ith and without work recovery from the expansion device. They reporte d an experimental coefficient of performance gain of 30%. They concluded that a significant di sadvantage to this type of compressorexpander was that the expander and compresso r pistons moved with identical strokes, which did not utilize all of the available expansion work (undere xpansion). The operating conditions were not detailed. Nickl et al. (2002) presented a second gene ration novel piston expandercompressor that would attempt to overcome the disadvantages of the expandercompressor presented by Heyl and Quack (1999). They developed a double rocker arm that would control the different speeds of the expander and compressor pistons. They conclude d that this mechanism would prove to be complex and expensive. A slight increase of the co efficient of performance relative to the first generation expandercompressor (Hey l and Quack, 1999) was realized. PAGE 40 40 Nickl et al. (2003) presented a third gene ration novel piston expandercompressor with three expansion stages for a transcritical CO2 Cycle. According to them, this would eliminate the identical strokes of the expander and compressor pistons (Heyl and Quack, 1999) in their first generation expandercompressor. It would also eliminate th e complex double rocker arm needed to control the different speeds of the e xpander and compressor pist ons (Nickl et al., 2002) of the second generation pist on expandercompressor. The authors first estimate of the isentropic efficiency of the expandercompressor was 85% and did not take into account losses due to heat transfer, pressure drops in valves internal leakage and friction losses. They concluded that the isentropic effi ciency of the expander decreased only 3% when these losses were taken into consideration. Zha et al. (2003) developed a rotarytype rolli ng piston expander to use as a throttle valve replacement in a transcritical CO2 cycle in small heat pumps and refrigeration systems. They experimentally determined the design paramete rs, method of control and determined the loss mechanisms associated with this expander. Th ey also mentioned that cavitation and liquid slugging are among the obstacles that hinder the development of CO2 expander technology. They have estimated the isentropic efficiency of the rolling piston expander to be about 50%. They have attributed the losses in efficiency to fr iction (~24%) and internal leakage losses (~25%). Fukuta et al. (2003) investigat ed and predicted the performa nce of a rotaryvane expander utilized in a transcritical CO2 cycle as a replacement to the thro ttle valve. They cited issues of slugging and cavitation as the main obstacles to the development of twophase expander technology. The prototype expander that was used had a builtin expansion ratio of 2:1. They initially assumed an expander efficiency of 60%. After taking into account the losses from heat transfer and internal leakage they calcul ated an isentropic efficiency of 43%. PAGE 41 41 Huff et al. (2002) developed an algorithm that estimates the performance of the expansion and compression process in positive displacement turbomachinery. They have taken into account internal leakage losses, heat tran sfer and valve losses in their m odeling effort. They have applied this analysis for scroll, piston, rotaryvane, rota ry piston and screw type mechanisms. They have applied this analysis with particul ar interest to a transcritical CO2 cycle and have reported a coefficient of performance gain of 4070% and a 515% increase in capacity. The authors discussed the importance of the builtin volume ratio of the expansion device in use and the effect it may have on the high side pressure of th e cycle. They concluded that if the rotational speed and builtin volume ratio of the device is not adjustable then this will ultimately reduce the benefit of the expander in a tr anscritical cycle. They proposed utilizing an expander and a throttling valve either in series or parallel to match the high side pre ssure with the optimum pressure. They concluded however that the perf ormance gain will be relatively less than if variable rotational sp eed and volume ratio were employed. Huff et al. (2003) experimentally investigated the use of two R134a scroll expanders in a transcritical carbon dioxid e cycle. The first prototype was mo dified by reducing the wall height of the original compressor scrolls. This modifica tion severely influenced this prototypes 28% isentropic efficiency. The highest isentropic and volumetric efficienci es that were reported were 42% (at 1800 rpm) and 68% (at 2200 rpm), respec tively, in the case of the second unmodified expander. Stosic et al. (2002) investigated the use of a twin screw combined compressor and expander for a high temperature transcritical CO2 refrigeration systems. They stressed the need to reduce bearing loads as this would make the expandercompresso r device more applicable to a larger range of pressures. Th ey achieved a 20% reduction in the bearing load by balancing the PAGE 42 42 loads of the compressorexpander rotors. They also concluded that throttling losses much larger than those associated with convent ional refrigerants exist in this helical type turbomachine. They reported an idealized 72% increase in the coe fficient of performance when applying this compressorexpander device to a high temperature transcritical CO2 refrigeration cycle. Hays and Brasz (2004) experi mentally investigated the use of a turbinecompressor mechanism in a 6 ton transcritical CO2 refrigeration or liquefaction cycle. The axial flow turbine previously presented in Hays and Brasz (1996) as a twophase expander is used to drive a compressor in a hermetic turbinecompressor unit. At a rotational speed of 10,000 rpm the turbine and compressor had efficiencies of 69 an d 80% respectively. The turbine had a measured efficiency of 56% at its maximum speed of 12,800 rp m. The vapor exiting the evaporator is then compressed in the turbinecompressor mechanism. The dual effects of expansion and partial compression in the turbinecompressor mechan ism increased the system coefficient of performance by 39%. Driver (1996) theoretically described the potential of utilizin g a compressorexpander device in a vapor compression system. Driver a nd Davidson (1999) have developed and tested a hingedvane compressorexpander unit for transcritical CO2 cycles. They found that if the compressorexpander device operated at a 100% isen tropic efficiency, whic h is highly unlikely, a COP improvement of 40% could be realized when compared w ith a conventional heat pump. The investigators pointed out that their compressorexpander device would not work with refrigerants such as R134a because of sizing issues. Preissner (2001) investigated the use of scroll expanders in a transcritical CO2 cycle. The author also performed an experimental compar ison of a conventional R134a and transcritical CO2 refrigeration cycles employing suction line heat exchangers. He found that CO2 cycles falls PAGE 43 43 short in performance by 8 and 23% for a range of typical operating conditions with particular emphasis on medium to high outdoor temperatures. With the implementation of a scroll expander the cycles have an identical coefficient of performance at a condensing temperature of 25oC. At higher condensing temperatures though, he found th at a significant perfor mance gap exists in favor of the R134a cycle. The author found inte rnal leakage losses to be the most significant loss mechanism due to limitations in machini ng accuracy and geometric design. The expander was thus not implemented in the cycles. Li et al. (2000) investigated the use of a vortex tube expans ion device in a transcritical CO2 refrigeration cycle. The vortex tubes ener gy separation effect, known as the RanqueHilsch effect, separates the high pressure gas entering th e vortex tube into two low pressure streams one at a low temperature and the other at a high temp erature. The authors compared this expansion device to a reciprocating piston expansion devi ce already developed by the authors. They concluded that an increase in the system coeffi cient of performance of 20% could be achieved if the piston expanders isentropic efficiency wa s 50%. The vortex tube expanders isentropic efficiency would have to be on the order of 38% to achieve the same performance gain. Heyl et al. (1998) developed a free piston compressorexpander unit to be employed in a transcritical CO2 cycle. They found that because of th e fullpressure principle a work extraction of 78% in relation to a complete expa nsion is obtained. Ertesv ag (2002) described the geometry and thermodynamics of a patented ro tarypiston machine that can be used as a compressorexpander device invented by K. Vadi ng. He mentioned the possible use of this concept in vapor compression systems. PAGE 44 44 Gas Refrigeration Cycles and Cryogenics The investigation of the use of expanders in gas refriger ation and cryogenic liquefaction cycles has been investigated by Gnutek (1979) Gnutek and Kalinowsk i (1986), and Baron and Trembley (2003). Gnutek (1979) analytically investigated the use of a ro taryvane expander in cryogenic liquefaction and vaporcompression gas refrigeration systems. The van der Waals equation of state was used to determine th e thermodynamic properties of the gas and therefore determine the performance of this expander de vice. The effects of friction, in ternal leakage losses and heat transfer from the ambient have been taken into consideration. Gnutek and Kalinowski (1986) described the use of a twostage rotaryvane compressor and a singlestage rotaryvane e xpander in a gas refrigeration un it using air as the working fluid. The authors obtained a oC evaporating temperature. Analy tical equations are presented to describe the performance of the expander. The au thors conclude that a ga s refrigeration system employing a rotaryvane expander and compressor w ould be significantly smaller in size than that utilizing a reciprocating piston compressor and expander. The work extracted from the expander was coupled to a generator. Baron and Trembley (2003) investigated the us e of indirect heat exchange and a turboexpander in a cryogenic refrigerator using liquid nitrogen as the re frigerant. According to the authors, heat transfer to the boi ling liquid nitrogen is critical in cryogenic applications in order to ensure that the latent heat of vaporization is maintained as high as possible. The authors theoretically found that an expa nder whose isentropic efficiency is 75% can increase the amount of heat transferred to the liqui d nitrogen by 28%. The authors di scussed the pros and cons of using scroll and rotaryv ane type expanders. The authors se lected a centrifugal turboexpander PAGE 45 45 because of compactness and cost. The authors estimated that a turboexpander should not exceed $10,000 in order to be economically viable. Expander Selection Although the concept of utilizing a compresso rexpander device is appealing, it cannot be applied to vapor compression and heat pump systems for the following reasons: The necessary builtin volume ratios of the compressor and expander are very different. The expander may have a volumeratio 78 times that of the compressor. There is an issue pertaining to the unequal inle t volume flowrates, which are a direct result of unequal inlet densities. Cavitation erosion and other complexities ma y arise from twophase expansion which is likely to affect the expansion efficiency and may also have a negative impact on the compression process and therefore greatly reduce the system COP. Baek et al. (2002) suggested that rotaryvane expanders ha ve an exceptional potential being utilized as expansion devices in refrigeration systems. This may be the case because of the fact that they may be mounted on the compressor shaft for ease of work recovery and have relatively less complicated va lve timing. Rotaryvane expand ers are also capable of accommodating higher rotational speeds. This transl ates into higher fluid handling capacity and hence a more compact device. Together with th e conclusions mentioned above by the different investigators, the potential of employing rota ryvane type expanders in conventional vapor compression systems/heat pumps is very promising. PAGE 46 46 CHAPTER 3 PARAMETRIC ANALYSIS OF CYCLES Models for the following refrigeration cy cles have been developed in FORTRAN90 utilizing REFPROP 7.0s R134a, R22, R12 a nd pure hydrocarbon property subroutines: Ideal singlestage cycle (henceforward referred to as the base cycle) A modified ideal singlestage cycle with an expansion device (the expansion device will henceforward referred to as ED) Actual singlestage cycle with and without an ED Ideal cycle with twostage compression and an economizer (henceforward referred to as the economizer cycle) A modified ideal economizer cycle with an ED Actual economizer with and without an ED Ideal cycle with an internal heat exchanger (henceforward referred to as the IHX cycle) A modified ideal IHX cycle with an ED Both the evaporating and condensing temperatures were varied for all 8 cases. The system COP, refrigerating efficiency, refrigerating capac ity, and required input work were found to be greatly dependent on the operating c onditions. It is of significant in terest to calculate the percent differences (system COP, refrigerating capacity a nd required input work) for the cycles with and without expansion devices. Ideal Cycles This section will describe both the therm odynamic processes involved with the base, economizer and IHX refrigeration cycles and the results when these cycles are modified by the addition of a twophase expander as a throttle valve replacement. PAGE 47 47 Base Cycle The single stage ideal vapor compression cycle is the simplest cycle and is the basis of most refrigeration and airconditioning technology. Th ese cycles have been utilized in cascade refrigeration systems to achieve higher c ondensing or lower evaporating temperatures. A schematic of the base cycle is shown in Figure 31. Both the Ts and Ph diagrams are shown in Figures 32. The base cycle consists of four processes that take place in the four components shown in Figure 31. Both the c ondensing and evaporat ing temperatures, Tc and Te, are initially known since they are usually design variables. This allows the computation of the corresponding high and low saturation pressures, Pc and Pe, of the cycle. The refrigerant at State 1 is ideally in a saturated vapor state (x1=1). The properties at Stat e 1 can be determined from P1=Pe and x1=1. In the base cycle, the refrigerant va por undergoes isentropic compression in the compressor and exits at State 2. The propertie s at this state are found utilizing the following assumptions: P2=Pc and s2=s1. The superheated refrigerant th en enters the condenser where it undergoes isobaric heat rejection. The exit, State 3, of the condenser is saturated liquid (x3=0). The properties at State 3 can be found by P3=Pc and x3=0. The saturated liquid refrigerant is then throttled in an expansion valve. This is an isen thalpic process. The propert ies at State 4 are thus determined from h4=h3 and P4=Pe. In the case where an expansion device is utilized as a throttle valve replacement, the saturated liquid under goes an isentropic e xpansion process. The properties at State 4 are thus determined from s4=s3 and P4=Pe. The two phase refrigerant then undergoes isobaric heat addition in the evaporator. The refrigerant is ideally saturated vapor at the exit of the evaporator. PAGE 48 48 The coefficient of performance for the base cycle and the base cycle with an expansion device (assuming the work output fr om the expander is ideally coupled to the compressor) are defined by Equations (31) and (32), respectively 14 21 in b compq hh COP whh (31) 14' ,exp exp2134'()()in b compq hh COP wwhhhh (32) Economizer Cycle The economizer cycle is modifi ed so that the compression and expansion processes are carried out in two stages. A liqui d/vapor separator increases the c ooling capacity of the cycle. A schematic of the Ts and Ph diagrams and cycle is shown in Figures 33 and 34, respectively. Both the condensing and evaporating temperatures, Tc and Te, are initially known since they are usually design variable s. This allows the computation of the corresponding high and low saturation pressures, Pc and Pe, of the cycle. The refrigerant at the evaporator exit, State 1, is saturated vapor. The properties at State 1 can be determined by x1=1 and P1=Pe. The saturated vapor then undergoes isentropic compression in the compressor. The properties at the 1st stage compressor exit, State 2, can be found by s2=s1 and P2=Pi, where Pi is the intermediate pressure of the cycle. Stoecker (1998) ha s stated that the optimum interm ediate pressure in a twostage compression process can be determin ed by the following relationship icePPP (33) The refrigerant at State 5, the condenser outlet, is saturated liquid. The properties at State 5 can thus be found from P5=Pc and x5=0. The refrigerant is th en either expanded by an isenthalpic process (h6=h5, P6=Pi) in the throttle valve or by an isentropic process in the expansion device (s6=s5, P6=Pi). The liquid (noted by f) a nd vapor (noted by g) are then PAGE 49 49 separated. The vapor in the amount of x is fed in to the inlet of the second compressor. The liquid in the amount of (1x) however is expanded again. The liquid refrigerant, at State 6f, is either expanded by an isenthalpic process (h7=h6f, P7=Pe) in the throttle valve or by an isentropic process in the expansion device (s7=s6f, P7=Pe). The twophase refr igerant then undergoes isobaric heat addition in the evaporator and is sa turated vapor at State 1. State 3 remains to be determined. An energy balance of the two str eams feeding into State 3 will determine the enthalpy at State 3 for the cases of isenthalpic and isentropic expansion processes as described by equations (34) and (35) respectively. 36662(1)ghxhxh (34) 36'6'6'2(1)ghxhxh (35) The properties at State 3 can then be determined from h3 and P3=Pi. The refrigerant at State 3 then undergoes isentropic compression in the second compre ssor. The properties at State 4 can then be determined from s4=s3 and P4=Pc. The coefficient of performance for the economi zer cycle and the economizer cycle with an expansion device (assuming the wo rk output from the expander is ideally coupled to the compressor) are defined by equations (36) and (37), respectively 617 ,1,262143(1)() (1)()()in econ compcompqxhh COP wwxhhhh (36) ,exp ,1,2exp,1exp,2 6'17' ,exp 6'214356'6'6'7'(1)() (1)()()()(1)()in econ compcomp econ fq COP wwww xhh COP x hhhhhhxhh (37) PAGE 50 50Internal Heat Exchanger (IHX) Cycle The internal heat exchanger (IHX) cycle is also known as the liq uidtosuction heat exchanger (LSHX) cycle. This cycle incorporat es a heat exchanger that subcools the saturated liquid leaving the condenser a nd superheats the saturated vapo r leaving the evaporator. A schematic of the IHX is shown in Figure 35. Bo th the Ts and Ph diagrams are also shown in Figures 36 respectively. Both the condensing and evaporating temperatures, Tc and Te, are initially known since they are usually design variable s. This allows the computation of the corresponding high and low saturation pressures, Pc and Pe, of the cycle. The analysis of the IHX cycle begins with the determination of States 3 and 6. The refrigerant is saturated vapor at the exit of the evaporator. The state properties may be determined from x6=1 and P6=Pe. Upon the refrigerant exiting the condenser, State 3, it is saturated liquid. The properties at this state point may be determined by x3=0 and P3=Pc. The effectiveness of the internal heat exchanger is defined as follows 16 max36 act IHXqTT qTT (38) For the case of the ideal cycle, the effectiveness is assumed to be equal to unity. This allows for the calculation of the temperature at State 1 (T1=T3). Using T1 and P1=Pe the other state properties may be determined. State 4 ma y be determined by performing an energy balance on the IHX, assuming the mass flow of refrigerant and the specific heat of the refrigerant are both constant, as follows 34611634qqTTTT (39) In the case of effectiveness equal to unity, T4=T6, the properties of the refrigerant at State 4 can be determined from T4 and P4=Pc. The superheated vapor at State 1 undergoes isentropic PAGE 51 51 compression in the compressor and exits at State 2. The properties at State 2 can be determined by s2=s1 and P2=Pc. The subcooled liquid at State 4 can either be put through isenthalpic expansion in the expansion valve (h5=h4, P5=Pe) or isentropic expansion in the expansion device (s5=s4, P5=P4). The twophase refrigerant then undergoes isobaric heat addition in the evaporator and exits as sa turated vapor at State 6. The coefficient of performance for the IHX cycle and the IHX cycle with an expansion device (assuming the work output from the expander to be ideally coupled to the compressor) are defined by equations (310) and (311) respectively 65 21 in IHX compqhh COP whh (310) 65' ,exp exp2145'()()in IHX compqhh COP wwhhhh (311) For the base cycle configurations (with a nd without an ED) at a constant condenser temperature (25oC), the percent increase realized in th e system COP was 8% to 19%, while an increase of 0.5% to 3.4% in refrigerating capac ity was realized. The evaporator temperature was varied from 12oC to 10oC. The required work input to th e compressor was found to decrease by 7.5% to 16%. For higher condenser temperatur es, the percent differences in the system COP were found to increase by 1021%, 1324%, 1527 % and 1830% for condensing temperatures of 30oC, 35oC, 40oC and 45oC, respectively. Actual Cycles The primary models: (1) simple vapor comp ression cycle; (2) vapor compression cycle with an economizer; and (3) vapor compression cycle with an internal heat exchanger, have been further modified to include the isentropic effi ciencies of both the compressor and expansion devices. The effects of superheating, subcooling and pressure drops (both in the line and in the PAGE 52 52 heat exchangers) as well as the effectiveness of the heat exchangers have also been considered. These effects would help achieve a more practical system model. For the actual base cycle system configurati ons (with and without an ED) and the case of constant condensing temperature (25oC) and varying evaporating temperature (12oC to 10oC), the percent increase realized of th e system COP was 3.4% to 8.9%, while an increase of 0.2% to 1.7% was realized in terms of the refrigerat ing capacity. The required work input to the compressor was found to decrease by 3.3% to 7. 2%. For a compressor efficiency of 85%, an expander efficiency of 50% and internal heat exchanger effectiveness of 70%, the values aforementioned are approximately half the values attained in the ideal case. The results for both the ideal and actual cycle improvements are presen ted in Table 31 and in Figures 37 to 313. It can be concluded from the preliminary re sults obtained that the maximum potential gain in the cycle coefficient of perf ormance is obtained for the base cycle. This conclusion supports the work of Robinson and Groll (1998a) who f ound that the stream availability following the heat rejection process in the conde nser is better utili zed by an expansion device rather than an internal heat exchanger. Alt hough improvements may be realized in the economizer cycle, the complexity and capitol cost of a twostage va porcompression system hi nder the utilization of this cycle with an expansion device. The following additional parametric inputs have been varied in order to determine the most important parameters when selecting the expa nsion device as well as the optimum operating conditions. Effect of Subcooling on System Performance The degree of subcooling that th e refrigerant undergoes in or after the condenser is a key factor that affects both the power requirem ent and the refrigerating capacity of a vapor compression refrigeration cycl e. Analysis of the effect of the degree of subcooling on the key PAGE 53 53 system performance parameters including the re frigerant effect, expander workoutput and overall system COP has been done. An increas e in the degree of subcooling was found to decrease the useful work output from the e xpander but increases the overall system COP by increasing the refrigerating e ffect. Figures 314 to 318 show the aforementioned trends. Among the most promising preliminary conclusions that may be drawn from this analysis is that cavitation erosion may be greatly reduced in the inlet of the expander since, depending on the degree of subcooling, the refrigerant enteri ng the expander may only be liquid. Hence, vapor will only start to form when the refrigerant ha s experienced a sizeable pressure drop in the expanders cavity (i.e. at large angular displacements). According to current literature, cavitation erosion in turbomachinery is prevalent at the inlet and the initial stages of compression and expansion due to the high velocity and com position associated with the incoming twophase flow. Effect of Superheating on System Performance The degree of superheat that the working fluid ex periences in the evaporator is critical in a vapor compression refrigeration syst em to ensure that the working fluid leaving the evaporator is completely vapor. Besides the well documented benefits of better compressor performance and longer service life, the following figures (Figures 319 and 320) analyze whether the degree of superheat has any significant effect on the system COP, refrigerating effect and the net work input to the system. A similar parametric analysis, as in the cas e of condenser subcooli ng, reveals that the increase in the degree of superheat in the evap orator does not significantly increase/decrease the work input into the system nor increase the re frigerating effect produced by the system. For a large degree of superheat such as 9oC, the gain in the refrigerating effect is roughly 5%. These PAGE 54 54 results are presented in Figures 319 and 320. There exists however a tradeoff between the degree of superheat and the heat exchanger area required in order to ach ieve that superheat. Evaluation of CFC, HFC and Transcritical CO2 Refrigeration Cycles Vapor compression refrigeration research has been significantly influenced by the elimination of ozonedepleting refrigerants su ch as chlorofluorocarbons (CFCs), the planned phase out of partially ozonedepleting refrigeran ts such as hydrochlor ofluorocarbons (HCFCs), and the interest in replacing what was once t hought to be harmless refrigerants such as hydrofluorocarbons (HFCs). Among the frontrunner s in replacing these refrigerants is carbon dioxide. A first and secondlaw based performan ce evaluation of conventional refrigeration and transcritical carbon dioxid e systems is presented here. The wo rking fluids investigated include R134a, R22 and R744 (CO2). The systems investigated incl ude the basic and modified vapor compression systems. The modified system consis ts of a twophase expansion device that is employed as a throttle valve replacement. The irreversibilities of the different system components in the basic and modified system s are presented. Comp arison of the potential increases in the refrigerating effect, reductions in the work required to operate the system and resulting increase in the system coefficient of performance are discussed. Comparison of the reductions/increases in cycle irreversibility and component contributions due to the employment of an expansion device are also discussed. Key expander operational parameters, such as the process volume ratio, are investigated. A recent revival of carbon dioxides use as a re frigerant has been given much attention in recently published literature. This arises from the need to replace ozone depleting CFCs and HCFCs and the global warming contributors HFCs. In comparison, carbon dioxide is naturally occurring and is thus an environm entally friendly refrigerant with an ozone depletion potential of zero. Published literature that discussed the re vival of carbon dioxides promise as a potential PAGE 55 55 candidate to replace CFCs and HFCs include s those of Lorentzen (1994), Lorentzen and Pettersen (1993). Due to the lo w critical temperature of CO2 however, 30.98oC, the heat rejection process typically takes place at a supercritical temperature in a ga s cooler cooled by ambient air. The critical pressure of CO2 is 7.38 MPa. This high heat rejec tion pressure requires a substantial increase in the compressor work required to achie ve it. This dramatically decreases the system coefficient of performance. Another inherent th eoretical limitation of the basic transcritical CO2 system is the fact that the refrigerant leaving the gas cooler may only be cooled to the ambient temperature. To overcome this, an internal heat exchanger may be utilized to provide a means of subcooling. In the case of a conventional va porcompression system, subcooling is typically obtained by increasing the area of h eat transfer of the condenser. It has been repo rted that the performance of transcritical CO2 systems suggests that the technol ogy is comparable to that of existing systems (Robinson and Groll, 1998). It ha s also been suggested that transcritical CO2 component technology must be optimized in orde r to meet the unique ope rational characteristics of carbon dioxide. This technology however differs significantly from conv entional refrigeration systems (Kim et al. (2004)). A lthough the stateofthea rt of transcritical CO2 systems is still far from optimum, the inherent thermodynamic performance of the basic transcritical CO2 system must be comparable to existing refrigeration t echnology. The system coefficient of performance, regardless of the technology used, may be incr eased by the utilization of expansion devices, liquidtosuction (internal) heat exchangers or performing compression in multiple stages, to name a few. In particular, many researchers have concluded that th e isenthalpic throttling process may be the largest source of irreversibility in a transcritical CO2 system. This section analyzes and compares the use of an expansion device as a throttle valve replacement in both conven tional and transcritical CO2 systems. There are two advantages to PAGE 56 56 using expansion devices with output work. The first is the fact th at lower enthalpy refrigerant is obtained at the inlet of the eva porator, which increases the refrig erating effect. The second is the extra work that can be extracted from the expansi on process, which can then be used to lower the input power requirement of the compressor. The degree of potential increase of the systems coefficient of performance however is greatly dependent on the isentropi c efficiency of the expansion device employed. Different expansio n devices have been suggested in recently published literature. Reduction of irreversibilitie s associated with the expansion process also leads to an increase in the secondlaw efficiency of the system. The extent of these improvements in both conventional systems u tilizing R22 and R134a as refrigerants and transcritical CO2 systems are presented and discussed. An abundant amount of literature dealing with modified refrigeration systems that employ expansion devices exists. For the purpose of this section, only the most pertinent of those studies are examined. Robinson and Groll (1998) analytically investigated and compared the performance of a transcritical CO2 system and a conventional R22 refrigeration system with and without an expansion turbine. Th ey found that the use of an inte rnal heat exchanger along with an expansion device decreased the COP of the transcritical CO2 system by 68%. They concluded that the stream availa bility following the heat rejection process in the condenser is better utilized by an expansion devi ce rather than an internal h eat exchanger. They also found a 23% COP increase when comparing an R22 system and a transcritical CO2 system both with expansion devices with an isentropic efficiency of 60% and when the system is operated at evaporating and condensing temperatures of 5 and 50oC, respectively. They concluded that a conventional R22 system employing an expans ion turbine outperforms all other systems including the transcritical CO2 system with an internal heat ex changer and an expansion turbine. PAGE 57 57 Preissner (2001) investigated the use of a sc roll expander in a transcritical CO2 system. He also performed an experimental comparison of conventional R134a and transcritical CO2 refrigeration systems employing suctionline heat exchangers. He found that the CO2 systems COP is 8 and 23% less than the R134a system fo r a range of typical ope rating conditions with particular emphasis on mediumtohigh outdoor te mperatures. With the implementation of a scroll expander the systems were found to have an identical co efficient of performance at a condensing temperature of 25oC. However at higher condens ing temperatures a significant performance gap existed in favor of the R134a system. Preissner (2001) found internal leakage losses to be the most significant loss mechanism due to limitations in machining accuracy and geometric design. The expander was thus not implemented in either system. Componentlevel models are needed for the an alysis of conventiona l and transcritical CO2 systems with and without an expansion device in place of a throttling valve. A general solution method has already been presented. Detailed componentlevel models that may include geometry, flow arrangement and loss mechanisms for the compressor, condenser, evaporator and expander may be developed separately and incor porated into this model when required. These componentlevel models will provide better estimat es of the isentropic efficiencies of the compressor and expander as well as the heat exch anger size and effectiveness of the condenser and evaporator, respectively. In the analysis describe d here, R22, R134a and CO2 are assumed to be the working fluids. The thermodynamic properties of these fluids are provided by means of coupling REFPROP 7.0s (Lemmon, 2002) property subroutin es with the models developed for this analysis. Pressure losses in all system components and throughout the systems piping have been PAGE 58 58 neglected. Figure 31 shows a schematic of a conventional and transcritical CO2 refrigeration system with and without an expansion device. The two systems utilize a compressor, an expansion device and an evaporator. The only component that differs is the device by which heat is rejected at the high pressure of the system. This component is a condenser in a conventional system and a gas cooler in the transcritical CO2 system. Figure 321 shows the Ts diagram of each system, respectively. Regardless of the refrigeration technology used, th e required input work to co mpress saturated vapor at the evaporating pressure to superheated vapor at the pressure of heat rejection is 2,1()s c chh w (312) The isentropic efficiency c of the compressor takes into account irreversibilities such as internal leakage and friction. Kim et al. ( 2004) reported that although leakage and frictional losses associated with carbon dioxi de compressors are lower, the current stateoftheart carbon dioxide compressor doesnt perform as well as a conventional refrigeratio n compressor. For the sake of comparison, isentropic efficiencies of current stateoftheart R22 and R134a compressors will be used to overestimate the performance of current CO2 compressor technology. This provides a tec hnologyindependent evaluation of the performance of the two systems. Selection of the supercritical heat rejection pressure is another vital operational parameter that significantly influences the opera tion and performance of a transcritical CO2 system. Pressure is independent of te mperature in the supercritical regime. According to numerous studies there exists a supercritical pressure at which the systems coefficient of performance is maximum. Both graphical and numerical simulati ons have been proposed to select this heat rejection pressure (Kauf, 1999). For the purpose of this st udy, the heat rejection pressure is PAGE 59 59 incrementally varied from the critical pressure (7.38 MPa) to 15 MPa until the optimum pressure at which heat rejection takes pl ace is determined for various op erating conditions. This procedure is performed for both basic and modified transcritical CO2 systems. In the case of a conventional refrigera tion system, the refrigerant undergoes desuperheating, condensation and subcooling in th e condenser. The effects of superheating and subcooling are considered when determining the heat exchanger effectiveness and the logarithmic meantemperature difference (LMTD). In the case of a transcritical CO2 system a gas cooler is employed to reject he at to the ambient and operates at a transcritical temperature and pressure. In an ideal gas cooler, the refr igerant temperature leaving the cooler, Tgc,out, would match the ambient temperature. The refrigerant en ters the cooler as a vaporlike substance and leaves as a liquidlike substance. Followi ng the conclusion of Robinson and Groll (1998) regarding the stream availability of the refr igerant leaving the cool er, no subcooling of the refrigerant is assumed. This allows for the maximum extraction of work during the expansion process. The heat rejected in the condenser or ga s cooler can be calculated as follows /2,3 condgcaqhh (313) where h2,a is the actual enthalpy of the superheated/s upercritical vapor calculated by means of the compressor isentropic efficiency. The enthalpy h3 is the enthalpy of the refrigerant leaving the heatrejecting device. For the purpo se of this study the refrigerant in the transcritical cycle is assumed to leave the gas cooler at a tran scritical pressure and temperature of T3=Tgc,out=Tamb+5. In the analysis of the conventional system the refrigerant is assumed not to experience any subcooling. The state properties thus correspond to the enthalpy of the saturated liquid at the PAGE 60 60 condenser saturation pressure. In this study the difference between the ambient temperature and the condensing temperature in the conve ntional system is assumed to be 15oC. In conventional and transcritical CO2 refrigeration systems a throttling/expansion valve is utilized to expand the refrigerant from the pressure of heat rejection to the evaporating pressure. This irreversible isenthalpic process may be replaced by the us e of an expansion device that would ideally expand the refrigerant in an isen tropic fashion. The potential increase in the system COP due to both the increase in the refrig erating effect and decrease in the cycle net work input have been studied ex tensively in recently published li terature for systems that utilize conventional refrigerants and transcritical CO2 as working fluids. Different positive displacement type expansion devices such as helicalscrew, scroll, rotaryvane and re ciprocating piston have been investigated. In this analysis, the type of expansion devi ce used is not specified. The type of device along with the geometrical and operational char acteristics may be programmed in separate subroutines that may provide actual performan ce predictions and an accurate estimate of the expanders isentropic efficiency. Depending on th e inlet conditions to the expander the actual work output from the expander can be expressed as 4,' 3()aeewhh (314) The use of expander work output can either be coupled to the compre ssor shaft or utilized to drive other auxiliary machinery or systems that may contribute other system improvements. This study considers only the al ternative of increased coolin g capacity brought on from near isentropic expansion and ideal coupling of the expander work to the compressor. The size of an expansion device is primarily a function of the builtin volume ratio of the expander. The expander should not only match (or be fairly similar to) the process expansion PAGE 61 61 ratio for typical system operating conditions but should also minimize the amount of wasted power recovery due to pressure losses incu rred during underexpansi on. The process volume ratio is defined as the ratio of the specific volume of the refrigerant at the inlet of the evaporator to the specific volume at the outlet of the conde nser/gas cooler. The expansion process in positive displacement expansion devices is comprised of the intake, expansion and the exhaust processes. The builtin volume ratio of an expande r is defined as the ratio of the specific volume at the start of the exhaust process to the specific vo lume at the end of the intake process. In this study it is assumed that both the builtin and proc ess volume ratios are identical and defined as follows 3 evapin vv r v (315) where vevap,in is the specific volume of the refrigerant after the expansion process (or at the inlet to the evaporator). Depending on the cycle analy zed, this state may correspond to an isenthalpic or nonisentropic expansion process. We will further assume that the degree of s uperheat the refrigerant experiences in the evaporator is assumed to be zero unless othe rwise indicated. For a given set of operating conditions the degree of superheat has much more of an influence on the overall performance of the system. The refrigerant is thus assumed to be saturated vapor upon exiting the evaporator unless otherwise indicated. An energy balance of the evaporator yields 4,' 1()aevapqhh (316) where h4,a is the actual enthalpy of the refrigerant entering the evaporator determined by means of the isentropic efficiency of the expande r. In the case of an unmodified cycle h4,a would be replaced by h4h=h3. PAGE 62 62 The coefficient of performance is defined as a ratio of the desired output to the required input. In the case of a modified vapor compressi on system with an expansion device, the net work input (compressor work less expander work ) is the required inpu t to the system. For simplicity, the work extracted from the expande r is assumed to be ideally coupled to the compressor. The COP is thus defined as e c evapw w q COP (317) A secondlaw based comparison of conventional and transcritical CO2 refrigeration systems is a far better comparison criterion. Exer gy or availability analys es reveal how closely actual refrigeration cycles are to ideal cycles. An exergy analysis also reveals the largest source of irreversibilities in the system by singling out th ose components that are most irreversible. The availability of a flowing fluid stream neglecting both kinetic and potential energy is defined as 000hhTss (318) The subscript 0 denotes a reference state at whic h the systems temperature and pressure are in equilibrium with its surroundings (T0=303.15 K ). This state is said to have zero availability if all other energy forms relative to the surroundings ar e zero. The specific irreversibility of a steadyflow device with heat transfer may be expressed as the difference between the reversible work and the actual work as follows 01revactinexitract rT I wwqw T (319) where qr and Tr are the specific heat transfer and the reservoir temperature at which heat is transferred to/from, respectively. The sign of qr depends on the direction of heat transfer. Utilizing Equations (318) and (319), the specific irreversibilities of the various components can be derived. The specific irrevers ibility of an adiabatic compressor may be written as follows PAGE 63 63 12,12,2,1 caaoa I hhTss (320) In the case of a conventional system, the sp ecific irreversibility of the condenser is 2,3032,32,1()()oo condacondaa rrTT IqTsshh TT (321) whereas, for a gas cooler, Tr in Equation (321) is replaced by the ambient temperature, Tamb. If the ambient temperature is identical to the refe rence temperature this e xpression would reduce to the difference in availability of the entering and leaving streams. If the expansion process is performed usi ng a throttling/expansion valve the specific irreversibility of that isenthalpic process is 4,3 voh I Tss (322) whereas in the case of utilizing an expansi on device, the specific irreversibility is ''' exp34,34,04,3 aaa I hhTss (323) The specific irreversibility of the evaporator for both systems is 4114411()oo evapevapo rrTT IqTsshh TT (324) A systems total irreversibility is the sum of the irreversibilities associated with its four components. Irreversibilities resulting from pre ssure drops in the systems components and transfer lines have been neglecte d. Irreversibilities asso ciated with heat tran sfer in the systems piping have also been neglected. Both first and secondlaw based evaluati ons of R22, R134a and transcritical CO2 refrigeration technology are critic al for selecting appropriate technology suitable for a specific application. For this purpose, simulation m odels for basic and modified vaporcompression refrigeration cycles have been developed. PAGE 64 64 The selection of the optimum heat rejection pressure is necessary to adequately compare transcritical CO2 systems to conventional systems. Ma ximum system COP occurs at the gas coolers optimum heat rejection pressure. Figure 322 illustrates the variat ion of the system COP as a function of the heat rejection pressure fo r both basic and modified systems at evaporating temperatures of 268 and 273 K. The COP of the basi c system can be seen as a near constant for heat rejection pressures greater th an the optimum heat rejection pressure. This is not the case for the modified system since higher heat rejection pr essures adversely affect the performance of the expansion device. For an evaporating temperat ure of 273K, it can be seen that the COP is maximum when the heat rejection pressure is 10.2 and 9.75 MPa for the basic and modified systems, respectively. For an evaporating te mperature of 268K the optimum heat rejection pressures were found to be 10.35 and 9.75 MPa for the basic and modified systems, respectively. The optimum heat rejection pressure can be de termined in a similar fashion for different evaporating temperatures and ope rating conditions. For all operat ing conditions investigated, the optimum heat rejection pressure has been assu med to be 10.2 MPa. A lthough the actual optimum heat rejection pressure may vary by as much as 5% over the entire range of evaporating temperatures investigated, the system COP deviat es by as much as 1 and 1.7% for the basic and modified systems, respectively. For the sake of computational time this deviation may be assumed negligible. Irreversibilities associated with the heat rejection and expansion processes are the largest sources of irreversibility in basic transcritical CO2 systems. Figure 323 il lustrates the variation of the percent of cycle irreversibility associated with the heat rejecti on and expansion processes as a function of the heat rejection pressure for basic and modified CO2 systems. For these operating conditions, the compressor and evaporator contribute approximately 1617 and 56% PAGE 65 65 of the basic cycles total irreversibility, respec tively. The compressor and evaporator contribute approximately 2227 and 910% of the modified syst ems total irreversibility, respectively. It can also be seen in Figure 323 that the throttle valve contributes 40 to 10% more to the systems total irreversibility when compared to the gas co oler at heat rejection pressures of 9 and 11.25 MPa, respectively. In contrast the contribution of irreversibility from the gas cooler is approximately 2% less and 25% more at heat rejection pressures of 9 and 11.25 MPa, respectively. The average irreversibilities of th e expansion and heat reje ction processes are 24% lower and 12.5% higher when comparing th e modified and basic transcritical CO2 systems, respectively. Component irreversibilities corresponding to an optimum heat rejection pressure are unlikely to be minimum. From Figures 322 a nd 323 it can be seen that the optimum heat rejection pressure corresponds to a maximum system coefficient of performance and a median value of the system irreversibility. A firstlaw based analysis of R22, R134a and transcritical CO2 systems is required to evaluate the thermodynamic performance of ba sic and modified refrigeration systems. Employing a twophase expansion device as a thro ttle valve replacement is the only modification made to the basic system. This allows for an unbiased comparison of the different refrigeration technologies. Figure 324 shows the variation of the coeffici ent of performance of basic and modified R22, R134a and transcritical CO2 systems as a function of the evaporating temperature. It can be seen that the COP of the cycles investigated in creases with increased evaporating temperature. The values of system COP for the basic and modified R22 systems are higher than those of R134 systems by as much as 6 and 0.6%, respecti vely. This maximum difference corresponds to PAGE 66 66 an evaporating temperature of oC. For the range of evaporati ng temperatures investigated, it can be seen that the COP of the basic transcritical CO2 system is lower than that of R22 by 3334% and that of R134a by 2934%. On the other hand, the COP of a modified transcritical CO2 system is lower than that of an R22 system by 17.522% and that of an R134a by 1821%. The COP of a modified transcritical CO2 system is still 4.29% less than that of a basic R22 system. The COP of a modified transcritical CO2 system is 2% higher and identical to that of a basic R134a system operating at evaporating temperatures of and oC, respectively. At higher evaporating temperatures, however the COP of a transcritical CO2 system is as much as 9% lower than that of a basic R134a system. When compared to similar R22 and R134a technology, the performance improvements of a modified transcritical CO2 system, in comparison to the basic system, are greater. Figures 325, 326 and 327, may further support this result. Fi gure 325 shows the difference in COP between the basic and modified R22, R134 and transcritical CO2 systems as a function of the evaporating temperature, respectively. It can be seen that the difference in COP decreases with increased evaporating temperature for all three syst ems. The decrease is not as rapid however for the transcritical CO2 system. As the evaporating temper ature decreases, the modified CO2, R134a and R22 systems outperform the basic systems by 2730%, 1023% and 918%, respectively. This increase in the COP can be attri buted to an increase in the refrigerating effect and a decrease in the input work required to operate the system. The refrigerating effect is defined as the spec ific evaporator capacity. From Figure 326, it can be seen that as the evaporating temperature decreases, the differences in the refrigerating effect of the modified and basic systems incr ease from 514%, 1.27% and 1.39% for the CO2, R134a and R22 systems, respectively. From Figure 327, the decrease of the required input to PAGE 67 67 the system can be seen to be dramatically di fferent. The work extracted from the expansion process is ideally utilized in the reduction of the input wo rk to the compressor. It can be seen that as the evaporating temperature increases, the di fference in required input work to operate a transcritical CO2 system increases. For increasing eva porating temperatures, the reduction in input work can be seen to be 2231%, 14.59% and 18.510% for transcritical CO2, R22 and R134a systems, respectively. When comparing th e basic and modified systems, the sizable differences in the increase in refrigerating effect and reduction of input work of CO2 point to favorable thermodynamic characteristics of CO2 when compared to t hose of R22 and R134a. When dealing with modified systems, the mo st favorable operational characteristic of CO2 is the volume ratio of the expander. This opera tional variable discussed earlier determines the size and practical feasibility of employing a tw ophase expansion device as a throttle valve replacement. Figure 328 shows the variation of the expansion devices volume ratio as a function of the evaporating temperature for CO2, R22 and R134a. As can be seen, there is a sizable difference between the volume ratios for the different working fluids. It can also be seen that the volume ratio decreases as the evapora ting temperature increases since the specific volume at the evaporator inlet decreases as temperature increases. For the evaporating temperatures reported (5 to 20oC only), the volume ratio can be s een to decrease from 2.71.6, 12.36.2, and 20.810 for transcritical CO2, R22, and R134a cycles, respectively. Efficient expansion devices are necessary to justify the cost and performance improvement of modified refrigeration syst ems when compared to conventi onal technology. This result is evident in Figure 329, which shows the di fference in COP of basic and modified CO2, R22 and R134a systems as a function of the expander s isentropic efficiency. In the case of CO2, it can be seen that the improvement in the system CO P increases in a much more dramatic fashion PAGE 68 68 when compared to R22 and R134a systems. The in crease in the system CO P can be seen to be 10.533%, 619% and 517% for CO2, R134a and R22 systems, respectively. A secondlaw based analysis is needed to de termine the irreversibil ities of the various components and to determine the increases/reducti ons in irreversibilities associated with any system modification. Figure 330 illustrates the component irreversibili ties of a modified R22 system as a function of the evaporating temper ature. As can be seen, for the modified R22 system, the largest sources of irreversibility are the condenser and compressor. Employing an expansion device has greatly reduced the irrevers ibilities associated with the basic systems throttling process. Component irreversib ilities for the basic and modified CO2, R134a and R22 systems at a specific operating condition are give n in Table 32. The table shows that the irreversibilities associated with the thrott ling process are reduced by 50, 18 and 16.5% for modified CO2, R134a and R22 systems, respectively. Similar figures and tables may be generated for various operating cond itions and system configurations. Figure 331 shows the percentage of system i rreversibility due to the condensing process for basic and modified R22 and R134a systems as functions of the evaporating temperature. The percentage of system irreve rsibility associated with the gas cooler for both the basic and modified transcritical CO2 systems are not included for clarity. It was found that the gas coolers contribution to the system irreversibility is fairly constant and averages 29.5 and 42% for the basic and modified transcritical CO2 systems, respectively. The figure also shows that the percentage of the total system irreversibility associated with the condensing process increases with evaporating temperature a nd with the use of an expansio n device for both R22 and R134a systems. This increase in irreversibility decreas es with increased evaporating temperatures from 106% and 116% for R134a and R22 systems, respectively. PAGE 69 69 Figure 332 shows the percentage of system i rreversibility associated with the expansion process for basic and modified CO2, R134a and R22 systems. As can be seen, the percentage irreversibility due to expansion is on aver age 47.5 and 24% for the basic and modified transcritical CO2 systems, respectively. An average valu e of 50% reduction in irreversible losses due to the addition of an expans ion device is expected with incr easing evaporating temperatures. Irreversibilities associated with the expansion pr ocess in R134a and R22 systems decrease with increased evaporating temperature and ma y be reduced from 2411% and 2210.5%, respectively. The ratio of the total system irreversibility to the heat rejection rate yields a dimensionless system irreversibility that may be used to evalua te and compare the total system irreversibilities of transcritical CO2, R22 and R134a systems. The heat re jection rate has been used to nondimensionalize the total system irreversibility since the only difference between conventional and transcritical refrigeration technology is the heat rejection device. Figure 333 shows the variation of this dimensionless quantity as a function of evaporating temperature for basic and modified CO2, R22 and R134a systems. As can be seen the basic and modi fied transcritical CO2 systems have the largest dimensionless cycl e irreversibilities associated with them. Modified R22 and R134a systems, on the ot her hand, have the least. The basic CO2 system and the basic R22 and R134a systems have fairly close dimensionless cycle irreversibilities. Theoretical simulation models have been deve loped to analyze and evaluate the first and secondlaw based performance of basic and modified R22, R134a and transcritical CO2 vapor compression refrigeration systems. The use of a twophase expansion devi ce as a throttle valve replacement is the only modification made to the basic system. This allows for an unbiased comparison of the different refrigeration technologies. Th e following conclusions can be made: PAGE 70 70 The optimum heat rejection pressure corres ponds to a maximum system coefficient of performance and a median value of system irreversibility. For the operating conditions investigated, the optimum heat rejection pressure of a modifi ed system is on average 5% lower than that corresponding to a basic transcritical CO2 system. The COP of basic and modified transcritical CO2 technology is inferior when compared to basic and modified R22 and R134a systems. The COP of basic and m odified transcritical CO2 systems are 29 to 34% and 17.5 to 22% lower than R22 and R134a systems, respectively. Modified transcritical CO2 systems can compete with basic R22 and R134a technology at lower evaporating temperatures but perform about 9% less at highe r temperatures. Favorable thermodynamic characteristics of CO2 are apparent when comparing the relative increases in COP and refrigera ting effect and the reduction in input work to R22 and R134a. For the range of evaporating temperatur es investigated, the improvement in the CO2 system COP is 12 to 18% when compared to R22 and R134a systems. An increase of 3.8 to 7% in refrigerating effect and a 7.5 to 22% decrease in input work were also realized when compared to R22 and R134a systems. The most favorable opera tional characteristic of CO2 is the volume ratio of the expander needed to expand the refrigerant to the evaporating pressure. At an evaporating temperature of 5oC the volume ratio of an R22 and R134a expander are 4.5 and 7.7 times that of a CO2 expander, respectively. Efficient expansion devices are necessary to justify the cost and performance improvement of modified refrigeration sy stems when compared to conventional technology. When compared to inefficient expansion devices (exp=25%), efficient expansion devices (exp=85%) may increase the system COP by 33%, 19% and 17% for CO2, R134a and R22 systems, respectively. The throttling process is the largest source of irreversibility in basic transcritical CO2 systems and the second largest in basic R22 and R134a systems. Irreversibilities may be reduced by as much as 50, 24 and 22% for modified CO2, R134a and R22 systems, respectively, employing a 65% efficient expansion device. The basic and modified transcritical CO2 systems have the largest total irreversibilities associated with them when compared to R22 and R134a systems. Performance and Size Optimization of Compression Refrigeration Systems A parametric analysis of key system operati onal variables in a modified vapor compression refrigeration system is presented in this section. A highly nonlinear relation ship is found to exist PAGE 71 71 between the many factors that influence the optimization of the systems coefficient of performance and the associated size a nd weight of a refrigeration system. Of these factors, the degree of subcooling that the refrigerant experi ences in the condenser is the most influential. It is the degree of subcooling that determines the necessary area of the heat exchanger required, ultimately affecting the size and the weight of a refrigeration system. The degree of subcooling also influences the size of the expander re quired to expand the refrigerant from the condenser pressure to the evaporator pressure. As the degree of subcooling increases, the resultant ratio between the outlet and inlet specific volumes decreases, and hence the builtin volume ratio of the expander would decrease. A decr ease in the latter causes a reduction in the expander size and weight. As the degree of subcooling increases, the us eful power output of th e expander (which may be coupled to the compressor) decreases. On th e other hand, this cause s the enthalpy of the refrigerant entering the evaporator to decrease. This causes an increase in the refrigerating effect of the system. The extent of the influence of th ese competing effects on the systems coefficient of performance needed further analysis. This was done using a simulation code developed for that purpose. An optimum degree of subcooling exists wher e the coefficient of performance of the system is a maximum and the size and weight of th e system are a minimum. It is recognized that the performance and compactness criteria may not be optimized simultaneously by a single subcooling choice. Furthermore, the penalties asso ciated with the increase of the heat exchanger area and the decrease of power out put of the expander should be mi nimized, while the benefits of the increasing refrigerating effect and the decr easing volumetric ratio of the expander should be maximized. PAGE 72 72 The quantification of the dependencies of the co efficient of performance, size, and weight of a vaporcompression system on design choice s such as the degree of subcooling are now presented. Component level models are needed for va porcompression systems that utilize an expander in place of the conventio nal throttling valve. A general solution method may be applied to model and validate experimental data and/or data provided by the manufacturers. The method presented is also applicable to both simple and modified vapor compression systems. Detailed componentlevel models that may include geometry, flow arrangement and loss mechanisms for the compressor, condenser, evaporator and expander may be developed separately and incorporated into this model when required. Th ese componentlevel models will provide better estimates of the isentropic efficiencies of bot h the compressor and expander as well as the heat exchanger size and effectiveness of the condenser and evaporator. In the analysis described in this section, R22 is assumed to be the worki ng fluid. The thermodynamic properties of R22 are provided by means of coupling REFPROP 7.0s pr operty subroutines with the model developed for this analysis. Pressure losses in all the sy stem components as well as throughout the systems piping have been neglected. Fi gure 31 shows a schematic of a simple vaporcompression cycle with and without an expansion device as a throttle valve replacement. In general, the required input work to compre ss saturated vapor at th e evaporating pressure to superheated vapor at the condensing pressure is given by Equation (312). The refrigerant undergoes desuperheating, condensation and su bcooling in the condenser. The effects of superheating and subcooling are considered when determining the heat exchanger effectiveness and the logarithmic meantemperature difference (LMTD). As a base case for comparing the effect of subcooling on system size and performa nce, the refrigerant l eaving the condenser is PAGE 73 73 assumed to be saturated liquid (i.e. no subcoo ling in the condenser). This represents the minimum heat exchanger area required to condense the refrigerant to a saturated liquid state and allow for the completion of the refrigeration cy cle. When subcooling is accounted for, the present analysis only investigates the subcooling th at the refrigerant experi ences in the condenser resulting from an increase in th e heat exchanger area. Other subc ooling methods such as utilizing a liquidtosuction heat exchange r or using integrated or mech anically dedicated subcooling loops are not analyzed in this study. The heat rejected in the condens er can be calculated as follows 3 2h h qa cond (325) where h2,a is the actual enthalpy of the superheated vapor calculated by means of the compressor isentropic efficiency. The enthalpy h3 is the enthalpy of the refrigerant leaving the condenser. In the base case this corresponds to the enthalpy of the saturated li quid at the condenser saturation pressure. In cases of subcooling this correspond s to the enthalpy of th e subcooled refrigerant determined at the saturation pr essure of the constanttempera ture condensing process and the temperature of the subcooled refrigerant. The effectiveness of the condens er is generally a f unction of the heat exchanger geometry, construction material and surface area. The effec tiveness of condensers and evaporators however is independent of flow arrangement since the re frigerant undergoes an isothermal phase change process. The effectiveness of the condenser is thus defined as ) ( ) (, min in c in cond in c out c c condT T C T T C (326) In the case of a condenser, the refrigerant typi cally has a very high h eat capacity because it is undergoing phase change. The coolant, on the other hand, experiences the maximum PAGE 74 74 temperature difference and ther efore its heat capacity is equal to the minimum heat capacity,min cCC In this case, the temperature of the coolant leaving the condenser, Tc,out, can be calculated as follows ) (, in c in cond cond in c out cT T T T (327) The relative size of the heat exchanger is calculated from the following Equation condlm condQUAT (328) where Tlm is the logarithmic mean temperature di fference, which is defined as follows out c in cond in c out cond out c in cond in c out cond lmT T T T T T T T T, , ,ln ) ( ) ( (329) Equation (329) is app licable to any heat exchanger flow arrangement since the refrigerant undergoes a phase change proce ss (i.e. correction factor F=1) (Incorpera 2002). In typical vapor compression refrigeration syst ems a throttling/expansion valve is utilized to expand the refrigerant from the condensing pressure to the evaporating pressure. This irreversible isenthalpic process may be replaced by the use of an expansion device that would ideally expand the refrigerant in an isentropic fa shion. The potential increase in the system COP due to both the increase in the re frigerating effect and decrease in the cycle net work input have been studied extensively in recent literature for systems that ut ilize conventional re frigerants and transcritical CO2 as working fluids. Many di fferent positive displacemen t type expansion devices such as helicalscrew, scroll, rotaryvane and reciprocating piston have been investigated. Here the type of expansion device used is not specified. The type of device along with the geometrical and operational charact eristics may be programmed in separate subroutines that may PAGE 75 75 provide actual performance predictions and an a ccurate estimate of the expanders isentropic efficiency. Depending on the degree of subcooling the refr igerant experiences in the condenser, the inlet conditions to the expander may be determined assuming that subcooling in the condenser occurs at a constant pressure. The actual work output from the expande r can be expressed as 4,' 3()seewhh (330) The size of an expansion device is primarily a function of the builtin volume ratio of the expander. The expander should not only match (or be fairly similar to) the process expansion ratio for typical system operating conditions, but should also minimize the amount of wasted power recovery due to pressure losses incu rred during underexpansi on. The process volume ratio is defined as the ratio of the specific volume of the refrigerant at the inlet of the evaporator to the specific volume at the outlet of the condenser. This volume ratio is expected to be smaller when the refrigerant leaving the condenser is subcooled. The complete expansion process in positive displacement expansion devices is comprised of the intake, expansion and the exhaust processes. The builtin volume ratio of an expande r is defined as the ratio of the specific volume at the start of the exhaust process to the specific volume at the end of the intake process. In this study it is assumed that both the builtin and proc ess volume ratios are identical and defined as .evapin v condoutv r v (331) We will further assume that the degree of s uperheat the refrigerant experiences in the evaporator is zero unless otherw ise indicated. For a given set of operating conditions, the degree of superheat has much more of an influence on the overall performance of the system. In this study, the impact of the degree of subcooling on the expander cy cle performance and size is of PAGE 76 76 primary interest. The refrigerant is thus a ssumed to be saturated vapor upon exiting the evaporator unless otherwise indicated. An energy balance of the evaporator yields 4,' 1()aevapqhh (332) where h4,a is the actual enthalpy of the refrigerant entering the evaporator determined by means of the isentropic efficiency of the ex pander. The COP is thus defined as e c evapw w q COP (333) The results presented here are in terms of dime nsionless quantities. This allows the reader to capture general trends of the analysis withou t the distraction of syst em specific calculations. The dimensionless groups that will be extensively used in the presentation of the results are defined as follows Dimensionless COP: refrenceCOP COP COP (334) Dimensionless expander work output: referencew w wexp, exp exp (335) Dimensionless expander volume ratio: reference v v vr r r, (336) Dimensionless condenser capacitance: referencem UA m UA m UA (337) For a vaporcompression system of known refr igerating capacity both the overall heat transfer coefficient, U, of a condenser with a constant effectiveness and the mass flowrate of refrigerant may be assumed constant. The condenser capacitance can thus be considered a direct PAGE 77 77 measure of the heat exchanger area required to reject a given heat load in the systems condenser if these two conditions are met. A constant cooling capacity comparison criter ion may also be used to constrain the analysis presented here. In the constant cooling capacity design scenario, the mass flowrate of refrigerant through the system would vary de pending on the degree of subcooling which will ultimately reduce the system component and pi pe sizing. The reduction in system size and weight would be significantly le ss, however, than that achieved by reducing the heat exchanger area. Figure 334 shows the variation of dimensionless condenser capacitance, expander volume ratio, expander work output and system COP as functions of the dime nsionless refrigerating effect. In this case, the refr igerant does not experience any subcooling in the condenser. The refrigerating effect is defined as the difference in the specific enthalpy of the refrigerant at the exit and the inlet of the evaporat or. For a given condensing temperat ure, the refrigerating effect increases as the evaporating temperature increases The data used to plot Figure 334 has been normalized by the refrigerating effect correspond ing to the lowest ev aporating temperature analyzed. It can be seen from Figure 334 that as the refrigerati ng effect increases (for instance due to an increase in the evaporating temperature) the system COP increases dramatically. This is due to the fact that as the difference in operating temperatures (or pressures) decrease both the compressor input work required and expande r work output decrea se. For the operating temperatures reported, the compressor work in put decreases by 74%, while the expander work output decreases by 84%. Furthermore, for the sa me temperature range, an increase in the refrigerating effect of 7.5% is observed. This re sults in an increase in system COP of about 75% when compared to a system operating at the lo west evaporating temper ature analyzed (223 K). PAGE 78 78 As the refrigerating effect increases, both the si ze and work output of th e expander decrease. As mentioned earlier, the expander work output decreases by about 84% whereas the expander volume ratio decreases by 92%. As the evaporat ing temperature increases, the benefits of utilizing an expander as a throttle valve repl acement become less significant. The condenser capacitance increases with the in crease in the refrigerating effect Over the full range of the refrigerating effect considered, the condenser capacitance can be seen to increase by 27%. Figure 335 shows the variati on in the dimensionless expa nder volume ratio and work output as functions of the eva porating temperature for different degrees of subcooling in the condenser. The expander volume ratio and work output decrease with an increase in the evaporating temperature and the degree of subcooling. At an ev aporating temperature of 278 K, typical in airconditioning applications, the expa nder volume ratio is found to be 8% and 16.4% less than the volume ratio corres ponding to the case of no subc ooling in the condenser for a degree of subcooling of 4oC and 8oC, respectively. The expander work output was found to be 15.3% and 29% less than the work output co rresponding to the case of no subcooling in the condenser for a degree of subcooling of 4oC and 8oC, respectively. Figure 336 illustrates the variation in the dimensionless condenser capacitance as a function of the evaporating temperature for differe nt degrees of subcooling in the condenser. It can be observed that as the degree of subcooli ng increases, the varia tion in the condenser capacitance increases dramatically For a typical airconditioning evaporating temperature of 273 K the condenser capacitance is found to be 24.6% and 54.3% greater than that corresponding to the case of no subcooling in the conden ser for a degree of subcooling of 4oC and 8oC, respectively. As previously mentioned, there exists a direct correlation between the heat exchanger area and the condenser capacitance. The increase in the heat ex changer area appears PAGE 79 79 to be much larger than the decrease in the e xpander volume ratio and wo rk output. The effects of system variables such as the isentropic efficien cies of the compressor and the expander, and the condensers effectiveness on the system COP, condenser capacita nce, expander volume ratio and work output are discussed below. Figure 337 shows the variation of the dimens ionless condenser capacitance as a function of the degree of subcooling for different values of the condensers eff ectiveness. The operating conditions and system variables are listed belo w Figure 337. For the cas e of no subcooling, the capacitance was found to be 25% and 56% larger for an eff ectiveness of 0.75 and 0.85, respectively, when compared to a system whose condenser has an effectiveness of 0.6. This results from the fact that as the effectivene ss increases, the exit coolant temperature, Tc,out, also increases, resulting in a decrease in the condensers LMTD. For a constant condenser heat load, this leads to an increase in conde nser capacitance. This increase is attributed to the increase of the heat exchanger effectiveness and does not take into account the increase in the heat exchanger area required to produce subcooling. This increase in condenser capacitance may result from either an increase in the overall he at transfer coefficient or an increase in the condensers area. For a condenser effectivenes s of 0.6 it is found that the capacitance must increase by 13% and 29.5% in order to produce a degree of subcooling of 4oC and 9oC, respectively. This represents an increase in the heat exchanger area of the same magnitude assuming that the overall heat transfer coefficien t of the condenser and the mass flowrate of the refrigerant are constant. For an effectiveness of 0.85 it is observed that in order to produce a degree of subcooling of 4oC and 9oC in the condenser, the capacitance must increase by 14.5% and 33%, respectively. The same trends are exp ected for different values of the ambient air temperature Tamb. PAGE 80 80 Figure 338 shows the variation of the dimens ionless expander work output as a function of the degree of subcooling in the condenser for different isentropic efficiencies of the expander. Detailed component level models of an expa nder would incorporate e ffects of friction and internal leakage losses a nd provide an accurate prediction of the expanders isentropic efficiency. As it can be seen, the work output from the e xpander decreases with both the decrease in isentropic efficiency and increase of the degree of subcooling. For an idea l expander utilized as a throttle valve replacement it can be s hown that a degree of subcooling of 5oC and 10oC results in a decrease of the work output of the expander by 19% and 35%, respectively, when compared to the case of no subcooling in the condenser. Expa nders whose isentropic efficiencies are 60% and 80% will theoretically produce le ss work than an ideal expander by that exact amount. An increase in the degree of subcooling in either ca se results in a decrease in the expander work output by 19% and 35% for a degree of subcooling of 5oC and 10oC, respectively. From this figure it can be concluded that in order to make the use of an expander as a throttle valve replacement beneficial, losses that affect the expanders isentropic efficiency as well as the degree of subcooling the refrigerant experien ces in the condenser must be minimized. Figure 339 shows the variation of the expander volume ratio as a func tion of the degree of subcooling for different isentropic efficiencies of the expander. The expander volume ratio is found to increase as the isentropi c efficiency of the expander d ecreases. Not only does the work output of the expander decrease, but also a larger expander adds both a we ight and size penalty to the modified vaporcompression system. For the case of an ideal expander, a degree of subcooling of 5oC and 10oC results in an increase in th e volume ratio by 10% and 20%, respectively. When compared to an ideal expand er, there exists a 1.67% and 3.33% increase in the volume ratio for the case of no subcooling in the condenser for expander isentropic PAGE 81 81 efficiencies of 0.8 and 0.6, respectiv ely. For a degree of subcooling of 10oC, this difference can be shown to decrease to about a 1.4% and 2. 8% increase in the expander volume ratio for isentropic efficiencies of 0.8 and 0.6, respectivel y, when compared to an ideal expander. It is observed that the decrease in th e expander work output is much more significant when compared to the increase in the expander volume ratio for both a decrease in the isentropic efficiency of the expander and the increase in the degree of s ubcooling the refrigerant experiences in the condenser. Figure 340 illustrates the variation of a system s dimensionless COP as a function of the degree of subcooling for different is entropic efficiencies of the expander. It is observed that as the degree of subcooling increases, the COP also increases by 2%, 3.4% and 4.7%. This is the case for 10oC of subcooling in the condenser for expa nder isentropic efficiencies of unity, 0.8 and 0.6, respectively when compared to the case of no subcooling. For the latter case, the COP is found to be 1.7% and 3.4% lower than that corresponding to an ideal expander for expander isentropic efficiencies of 0.8 and 0.6, respectively. It may thus be concluded that the variation in COP is significant for larger values of subcoo ling in the condenser and then becomes more significant as the isentropic efficiency decr eases. Figure 341 shows the variation of the dimensionless COP as a function of the degree of subcooling for different degrees of superheat in the evaporator. The system parameters are assumed constant and are liste d below the figure. Superheatin g is beneficial to prevent compressor slugging. An increase in the degree of superheating is generally associated with an increase in the refrigerating effect and an in crease in the input compressor work required to compress the superheated vapor to the condensing pressure. It is observed that as the degree of subcooling increases, the COP increases for all valu es of superheating analyzed. It is also noted PAGE 82 82 that as the degree of superheat increases the COP is seen to decrease. This may be associated with a significant increase in th e compressor input work in contra st to gains in the refrigerating effect. For the case of no subcooling in the cond enser it may be shown that as the degree of superheat increases, th e compressor input work increases by 2.8% and 5.3% whereas the refrigerating effect increases by 2.4% a nd 15.8% for a degree of superheat of 5oC and 10oC, respectively. The degree of superheat has no direct impact on the performance or size of either the condenser or expander. The de gree of superheat should be sele cted and minimized in order to maximize a given COP. The analysis presented in this section provides a founda tion for applicationspecific optimization. The degree of subcooling the refrige rant experiences in a sy stems condenser has a significant effect on the size and performance of a vaporcompression system utilizing twophase expanders as throttle valve replacements. The findings of this analysis are as follows As the evaporating temperature increases the bene fits of utilizing an expander as a throttle valve replacement become less significant. This can be attributed to significant decreases in the expander volume ratio and work output. The expander volume ratio and work output also decrease with increased condenser subcooling. The work output from the expander decrease s with both the decrease in isentropic efficiency and the increase of the degree of subcooling. Losses that affect an expanders isentropic efficiency as well as the de gree of subcooling must be minimized. The decrease in the expander work output is much more significant when compared to the increase in the expander volume ratio for both a decrease in the isentr opic efficiency of the expander and the increase in the degree of subcooling. The variation in system COP is significant for larger values of subcooling in the condenser and become more significant as the expande rs isentropic efficiency decreases. The degree of superheat in the evaporator has no direct impact on the performance or size of either the condenser or expander. The degree of superheat should be selected and minimized in order to maximize a given systems COP. PAGE 83 83Pure Hydrocarbons as Refrigerants Hydrocarbons are very lucrative as refrig erant replacements for CFCs, HCFCs and HFCs since they are abundant, inexpensive and enviro nmentally friendly because they have no ozone depletion potential. Among the major drawbacks of using hydrocarbons as refrigerants is their high flammability potential. This limits their use to hermetic systems and the slightest leak of a hydrocarbon refrigerant may prove to be catastr ophic. The following is a review of recent literature pertaining to the use of hydrocarbons as pure refrigeran ts, in mixtures, and issues pertaining to flammability. The most promis ing potential hydrocarbons used as refrigerant substitutes are listed in the Table 33 along with pertinent fluid information. Many researchers have investigated th e performance of pure hydrocarbons and hydrocarbon mixtures as refriger ants. According to Granryd (2001) several standards allow the use of hydrocarbons as refrigerants in internally safe, hermetically sealed systems with a charge limit of 0.15 kg. This limits the use of hydro carbons to domestic refrig erators and freezers and low capacity heat pumps. Larger refrigeration sy stems may utilize hydroca rbons as refrigerants as long as there is adequate exhaust and extrem e safety precautions are in place. According to Granryd (2001) hydrocarbons are compatible with conventional materials used to construct vaporcompression refrigerating systems. Granryd (2001) theoretically inve stigated various cycle and heat transfer characteristics for various hydrocarbon refrigerants including propane, butane, isobut ene, propene (propylene), cyclopropane, Dimethyl ether a nd a 50% propane50% isobutane mixture. The results were compared with cycle and heat transfer char acteristics of R12, R22 and R134a. The author found that the pressure ra tios associated with butane and isobu tene are higher while propane and cyclopropane are lower than that of R22, respectively. The author also notes that in the case of using butane and isobutane as refrigerants, a nece ssary degree of superh eat is required at the PAGE 84 84 evaporator exit to ensure that isentropic comp ression doesnt move the va por into the twophase region. When comparing the cycle coefficient of performance to the Carnot efficiency, butane was found to have the highest cy cle Carnot efficiency. Granr yd (2001) also experimentally investigated the use of propane in a refrigeration unit and compar ed its cycle performance with that of R12, R22, R134a and R152a. He concl uded that a 35% increase in system COP and a 315% decrease in refrigerating capacity exists when propane is compared to conventional refrigerants. He attributed the decrease in co mpressor work to the lower molecular weight of propane. The use of pure hydrocarbons and mixtures as re frigerants in domestic refrigerators has been investigated by Hammad a nd Alsaad (1999), Jung et al. (2000), Tashtoush et al. (2002), Sekhar (2004) and Wongwises and Chimres (2005). Purkayastha and Bansal (1998) presented an e xperimental study of utilizing propane and a LPG mix (by mass fraction: 98. 95% propane, 1.007% ethane and 0.0397% isobutane) as a suitable replacement for R22 in a heat pump. They found an increase in system coefficient of performance of 18 and 12%, and 9 and 4% for pr opane and LPG, respectively. These values correspond to condensing temperatures of 35oC and 55oC, respectively, at an evaporating temperature of 3oC. Colbourne and Suen (2004a, 2004b) appraised the flammabili ty hazards of hydrocarbon refrigerants in refrigeration and heat pump systems. Dlugogorsk i et al. (2002) experimentally investigated the use of inerti ng agents with natural gas and a propanebutane mixture. Their recommendations however have not been tested experimentally in a refrigeration unit. In the case of pure hydrocarbon refrigerants th e parameters under investigation include the system coefficient of performance, refrigerati ng effect, work consumption by the compressor and PAGE 85 85 the effect of both subcooling and superheat on sy stem performance. The case where an expander is utilized as a throttle valve replacement was also investigated. Comparisons with R12, R22 and R134a were also made to compare the perfor mance of pure hydrocarbons as refrigerants in both the conventional and modified cycles. The re sults from these simulations are presented in Figures 342 to 347. PAGE 86 86 Figure 31. A schematic of the id eal base cycle (12341) and th e modified base cycle with an expansion device (12341) wcomp qout 1 2 3 4 4 Te,Pe Tc,Pc qin wexp PAGE 87 87 Figure 32. Ts and Ph diagrams of th e ideal base cycle (12341) and the modifi ed base cycle with an expansion device (1 2341) s T 1 2 3 44 P h 1 2 3 4 4 PAGE 88 88 Figure 33. Ts and Ph diagrams of the economizer cycle (1 2345671) and an economizer cycle with an expansion device as a throttle valve replacem ent (12345671) Pe s T Pc Pi 1 2 3 4 5 4 6 6 6f 5 7 7 h P Te Ti 34Tc 1 5 6 6f 7 7 2 PAGE 89 89 Figure 34. A schematic of the economizer cycle (12345671) and an economizer cycle with an expansion device as a throttle valve replacement (12345671) qout 2 5 4 Te,Pe qin Tc,Pc wcomp,1 wcomp,2 1 6 3 6g or 6g 7 7 wexp,2 6 wexp,1 6f or 6f Separator x (1x) PAGE 90 90 Figure 35. A schematic of th e IHX cycle (1234561) and the modified IHX cycle with an expansion device as a throttle valve replacement (1234561) wexp 5 5 6 Tc,Pc wcomp q ou t 2 3 Te,Pe q in 1 4 IHX PAGE 91 91 Figure 36. Ts and Ph diagra ms of the IHX cycle (1234561) and the modi fied IHX cycle with an expansion device as a th rottle valve replacement (1234561) T 6 23 1 55 1For: =1 T1=T3 T4=T6 4 s P h 6 2 35 5For: =1 T1=T3 T4=T6 14 PAGE 92 92Table 31. Summary of the percent changes in the system COP, refrigerating capacity and required work input by the addition of an expansion device for the ideal and actual R134a singlestage, economizer and IHX cycles c=85%, exp=0.5, IHX=0.7 ** a decrease in the amount of work needed theoretically *** maximum value corresponds to Te=20oC and minimum value corresponds to Te=10oC Ideal*** Actual *,*** Tc, oC Evaporating Range COP, % Qe Wnet, COP, % Qe Wnet, 25 20oC to 10oC 818.7 0.43.4 7.615.9 3.48.3 0.21.7 3.37.2 30 20oC to 10oC 10.321.4 0.764.3 9.617.8 4.59.6 0.42.2 4.38.2 35 20oC to 10oC 12.924.2 1.25.4 11.920 5.611 0.62.8 5.39.2 40 20oC to 10oC 15.627.1 1.86.7 1422 6.812.4 0.93.5 6.410.3 Base Cycle 45 20oC to 10oC 18.530.2 2.48.2 16.524 8.214 1.24.3 7.511.4 25 20oC to 10oC 5.211 0.31.7 4.99 2.24.8 0.21.4 2.13.7 30 20oC to 10oC 6.512 0.52 6.110.2 2.95.6 0.41.7 2.64.1 35 20oC to 10oC 8.114 0.72.6 7.411.4 3.56.4 0.52.2 3.24.6 40 20oC to 10oC 9.615.5 13.2 8.812.7 4.37.3 0.82.7 3.75.1 Economizer Cycle 45 20oC to 10oC 11.417.4 1.33.9 10.214.1 5.18.3 1.13.3 4.35.6 25 20oC to 10oC 2.63.6 0.140.6 2.53 1.62.9 0.10.6 1.52.4 30 20oC to 10oC 33.9 0.20.7 2.83.3 1.93.3 0.20.7 1.82.7 35 20oC to 10oC 3.44.5 0.31 3.233.7 2.33.7 0.20.9 2.12.9 40 20oC to 10oC 3.95 0.41.2 3.64 2.74.2 0.61.1 2.43.2 IHX Cycle 45 20oC to 10oC 4.45.5 0.61.4 44.4 3.14.7 0.51.4 1.73.5 PAGE 93 93 Figure 37. Variation of COP, between the modified cycle with an expansion device and the ideal cycle (R134 a), with evaporating temperature for A) Tc=25oC, B) Tc=45oC for the base, economizer and IHX cycles 0% 2% 4% 6% 8% 10% 12% 14% 20246810Evaporating Temperature, oCIncrease in COP Base Tc=25C Economizer Tc=25C IHX Tc=25C 0% 5% 10% 15% 20% 25% 30% 20246810Evaporating Temperature, oCIncrease in CO P Base Tc=45C Economizer Tc=45C IHX Tc=45CA B PAGE 94 94 Figure 38. Variation of Qe and Wnet, between the ideal modi fied cycle with an expansion device and an ideal base cycl e, with evaporating temperature for various condenser temperatures in a singlestage vaporcompression refrigeration unit (nega tive denotes a reduction). 25% 20% 15% 10% 5% 0% 5% 10% 20246810Evaporating Temperature, oCChange in Refrigerating Effect and Net Wor k Tc=25C Tc=30C Tc=35C Tc=40C Tc=45C Qe Wnet PAGE 95 95 Figure 39. Variation of COP, between the modified cycl e with an expansion device and the ideal cycle, as a function of the evaporating temperature for both R22 and R134a for various expander efficiencies Tc=45oC (comp=85% when not ideal) 0 5 10 15 20 25 20246810 Evaporating Temperature, oC COP R134a, Ideal R22, Ideal ex p =1 ex p =0.75 ex p =0.5 PAGE 96 96 Figure 310. Variation of COP, between the modified cycl e with an expansion device and the ideal cycle, as a function of the evaporating temp erature for various condenser temperatures for the actual and ideal cycle configurations of the economizer cycle. 0% 2% 4% 6% 8% 10% 12% 14% 16% 18% 20% 20151050510Evaporating Temperature, oCChange in COP Actual, Tc=25C Actual, Tc=45C Ideal, Tc=25C Ideal, Tc=45C comp=85%, exp=0.5 PAGE 97 97 Figure 311. Variation of COP, between the modified cycl e w/ an expansion device and the ideal cycle, as a function of the evaporating temperature for various condenser temperatures for the actual and ideal cycle configurations of the IHX cycle 0% 1% 2% 3% 4% 5% 6% 20151050510Evaporating Temperature, oCChange in COP Actual, Tc=25C Actual, Tc=45C Ideal, Tc=25C Ideal, Tc=45C comp=85%, exp=0.5, IHX=0.7 PAGE 98 98 Figure 312. Variation of refr igerating efficiency as a function of the evaporating temperature for both the base (no expa nder) and ideal and actual modified cycle with and an expander at a condenser temperature of Tc=45oC Figure 313. Variation of refrigerating e fficiency as a function of the evaporating temperature for the actual base, IHX a nd economizer cycles with an expander at a condenser temperature of Tc=25oC 0.75 0.8 0.85 0.9 0.95 1 20246810Evaporating Temperature, oCRefrigerating Efficienc y R134a R22 exp=1 exp=0.75 No Expander comp=85%, exp=0.5, IHX=0.7 0.4 0.5 0.6 0.7 0.8 0.9 20151050510 Evaporating Temperature, oCRefrigerating Efficiency Actual, IHX Cycle Actual, Base Cycle Actual, Economizer Cycle oC PAGE 99 99 4 6 8 10 12 14 16 02468 Tsubcooling, oCCOP Tc=25C Tc=30C Tc=35C Tc=40C Tc=45C Figure 314. Variation of an ideal system s COP as a function of the degree of subcooling for various c ondensing temperatures (Te=5oC, Tsh=0 oC) PAGE 100 100 Figure 315. Variation of an ideal system s COP as a function of the degree of subcooling for various condenser temp eratures and expa nsion processes (Te=5oC, Tsh=0oC) 0 2 4 6 8 10 12 14 16 0246810 Tsubcooling, oCCOP Isenthalpic Expansion Isentropic Expansion Tc=25oCTc=45oC PAGE 101 101 Figure 316. Variation of the refrigerati ng effect as a function of the degree of subcooling for various condenser temp eratures and expa nsion processes (Tsh=0oC) 100 120 140 160 180 200 02468 Tsubcooling, oCRefrigerating Effect, kJ/ k Isenthalpic Expansion Isentropic ExpansionTc=45oCTc=25oC PAGE 102 102 10 14 18 22 26 30 579111315Evaporator temperature, oCCOP 0 C sc, Isenthalpic 5 C sc, isenthalpic 0 C sc, Isentropic 5 C sc, Isentropic Figure 317. Variation in an ideal system s COP with respect to the evaporator temperature for different degrees of subcooling and expansion processes (Tsh=0oC) PAGE 103 103 Figure 318. Variation of the difference in system COP,%, between the ideal cycle and modified cycle with an expansion de vice as a function of the evaporator temperature for various condenser temp eratures and degrees of subcooling (Tsh=0oC) 0 5 10 15 20 25 579111315Evaporator temperature, oC COP 0C 0C 5C 5CTsc Tc=25oC Tc=45oC PAGE 104 104 0 5 10 15 20 25 02468 Tsuperheat, oC COP Tc=25C Tc=35C Tc=45C Figure 319. Variation of the difference of th e system COP, %, base cycle and modified cycle with an expansion device as a func tion of the degree of superheat in the evaporator for various condenser temperatures. PAGE 105 105 100 120 140 160 180 200 02468 Tsuperheat, oCRefrigerating Effect, kJ/kg Tc=25C Tc=35C Tc=45C Figure 320. Variation of the re frigerating effect for an idea l cycle as a function of the degree of superheat for vari ous condenser temperatures PAGE 106 106 Figure 321. Ts diagram of the ba sic system (12341) and the modified system with an expansion device (12341) for a A) conventional refriger ation system and B) transcritical CO2 refrigeration system s T 1 2s 3 4 s 4 a 4 h 1 2 a Pe vapPcond s T 1 2s 3 4s 4a 4h 2a Pevap Pgc CP A B PAGE 107 107 Figure 322. Variation of system coefficien t of performance as a function of heat rejection pressure for various evaporati ng temperatures for basic and modified transcritical CO2 systems Figure 323. Percentage of cycl e irreversibility associated with the heat rejection and expansion processes as a function of h eat rejection pressure for basic and modified transcritical CO2 systems 1.5 2 2.5 3 3.5 99.51010.51111.5 Heat Rejection Pressure, MPa COP Te=273 K Te=268 K Te=273 K Te=268 K Modified System Basic System 0 10 20 30 40 50 60 99.51010.51111.5 Heat Rejection Pressure, MPaIrreversibility % Gas cooler Valve Gas cooler Expander comp=0.85 exp=0.65 T3=313 K Tevap=273 KBasic System Modified System PAGE 108 108 Figure 324. Coefficient of performance of basic and modified R22, R134a and transcritical CO2 systems as functions of the evaporating temperature Figure 325. Difference in coefficient of pe rformance between basic and modified R22, R134a and transcritical CO2 systems as functions of the evaporating temperature 0% 5% 10% 15% 20% 25% 30% 35% 3025201510505 Evaporating Temperature, oC COP R744 R134a R22 comp=0.85 exp=0.65 Tamb=35oC Tcond=50oC Tgc_out=40oC 1 2 3 4 5 3025201510505 Evaporating Temperature, oCCOP Basic R744 System Modified R744 System Basic R134a System Modified R134a System Basic R22 System Modified R22 Systemcomp=0.85 exp=0.65 Tamb=35oC Tcond=50oC Tgc_out=40oC PAGE 109 109 Figure 326. Difference in refr igerating effect between basi c and modified R22, R134a and transcritical CO2 systems as functions of th e evaporating temperature Figure 327. Difference in system input work between basic and m odified R22, R134a and transcritical CO2 systems as functions of the evaporating temperature (negative denotes a decrease) 0 0.04 0.08 0.12 0.16 3020100 Evaporating temperature, oC Refrigerating Effect R744 R134a R22comp=0.85 exp=0.65 Tamb=35oC Tcond=50oC Tgc_out=40oC 30% 20% 10% 0% 3020100 Evaporating Temperature, oC Input Work R744 R134a R22comp=0.85 exp=0.65 Tamb=35oC Tcond=50oC Tgc_out=40oC PAGE 110 110 Figure 328. Volume ratio of the expande r employed in modified R22, R134a and transcritical CO2 systems as functions of the evaporating temperature Figure 329. Difference in coefficient of pe rformance between basic and modified R22, R134a and transcritical CO2 systems as functions of expander isentropic efficiency 0 5 10 15 20 25 5101520 Evaporating Temperature, oCVolume Ratio R134a R744 R22comp=0.85 exp=0.65 Tamb=35oC Tcond=50oC Tgc_out=40oC 5% 10% 15% 20% 25% 30% 35% 25%45%65%85% Expander Isentropic Efficiency COP R744 R134a R22comp=0.85 Tamb=35oC Tcond=50oC Tgc_out=40oC Tevap=0oC PAGE 111 111 Figure 330. Percentage of cycl e irreversibility due to variou s components in a modified R22 system as functions of the evaporating temperature Figure 331. Percentage of cy cle irreversibility due to condensing process in basic and modified R22 and R134a systems as functions of the evaporating temperature 0 10 20 30 40 50 3020100 Evaporating Temperature, oCIrreversibilty, % Compressor Condenser Expander Evaporatorcomp=0.85 exp=0.65 Tamb=35oC Tcond=50oC 20 25 30 35 40 45 50 3020100 Evaporating Temperature, oCCondenser Irreversibility, % Basic R134a System Modified R134a System Basic R22 System Modified R22 Systemcomp=0.85 exp=0.65 Tamb=35oC Tcond=50oC PAGE 112 112 Figure 332. Percentage of cycl e irreversibility due to the expansion process in basic and modified R22, R134a and transcritical CO2 systems as functions of the evaporating temperature Figure 333. Dimensionless system irreversib ility in basic and m odified R22, R134a and transcritical CO2 systems as functions of th e evaporating temperature 0 10 20 30 40 50 60 3020100 Evaporating Temperature, oCExpansion Process Irreversibility, % Basic R744 System Modified R744 System Basic R134a System Modified R134a System Basic R22 System Modified R22 Systemcomp=0.85 exp=0.65 Tamb=35oC Tcond=50oC Tgc_out=40oC 0.1 0.15 0.2 0.25 0.3 0.35 3020100 Evaporating Temperature, oCTotal Irreversibility/Heat Rejection Rate Basic R744 System Modified R744 System Basic R134a System Modified R134a Syste m Basic R22 System Modified R22 Systemcomp=0.85 exp=0.65 Tamb=35oC Tcond=50oC Tgc_out=40oC PAGE 113 113 0 1 2 3 4 11.021.041.061.08Dimensionless refrigerating effectDimensionless quantit y condenser capacitance expander volume ratio expander work output COP Table 32. Percentage of cycl e irreversibility due to the va rious components in basic and modified R22, R134a and transcritical CO2 systems Figure 334. Variation of di mensionless COP, expander work output, expander volume ratio and condenser capacitance as a f unction of dimensionless refrigerating effect. Tcond=45oC, Tamb=25oC, cond=0.75,comp=0.85,exp=0.75 R744R134aR22R744R134aR22 Compressor, %17.322.221.424.628.226.3 Condenser, %33.638.142.646.7 Gas cooler, %29.742.2Expansion valve, %46.53329Expander, %23.214.612.5 Evaporator, %6.511.211.51014.614.5 Basic SystemModified System PAGE 114 114 Figure 335. Variation of dime nsionless expander work output and expander volume ratio as a function of evaporating temperatur e for various degrees of subcooling in the condenser. Tcond=45oC, Tamb=25oC, cond=0.75,comp=0.85,exp=0.75 Figure 336. Variation of dimensionless condenser capacitance as a function of evaporating temperature for various de grees of subcooling in the condenser. Tcond=45oC, Tamb=25oC, cond=0.75,comp=0.85,exp=0.75 0 0.2 0.4 0.6 0.8 1 40302010010 Evaporating temperature, oCDimensionless wexp and rv 0 4 8 0 4 8Degree of Subcooling, oCdimensionless rvdimensionless wexp 0 1 2 3 40302010010 Evaporating temperature, oCDimensionless condense r capacitance 0 4 8Degree of Subcooling, oC PAGE 115 115 Figure 337. Variation of dime nsionless condenser capacitance as a function of degree of subcooling in the condenser for various values of condenser effectiveness. Tcond=45oC, Tevap=5oC, Tamb=25oC,comp=0.75,exp=0.75 Figure 338. Variation of dime nsionless expander work output as a function of degree of subcooling in the condenser for various expander efficiencies. Tcond=45oC, Tevap=5oC, Tamb=30oC, cond=0.75,comp=0.85 1 1.4 1.8 2.2 2.6 02468 Degree of subcooling, oCDimensionless condense r capacitance 0.6 0.75 0.85 Condenser effectiveness 0.3 0.5 0.7 0.9 0246810Degree of subcooling, oCDimensionless expander work output 1 0.8 0.6 Expander efficiency PAGE 116 116 Figure 339. Variation of dime nsionless expander volume ratio as a function of degree of subcooling in the condenser for various expander efficiencies. Tcond=45oC, Tevap=5oC, Tamb=30oC, cond=0.75,comp=0.85 Figure 340. Variation of dime nsionless COP as a function of degree of subcooling in the condenser for various expander efficiencies. Tcond=45oC, Tevap=5oC, Tamb=30oC, cond=0.75,comp=0.85 0.92 0.96 1 1.04 0246810Degree of subcooling, oCDimensionless COP 0.6 0.8 1Expander efficiency 0.8 0.85 0.9 0.95 1 1.050246810 Degree of subcooling, oCDimensionless expander volume ratio 1 0.8 0.6 Expander efficiency PAGE 117 117 Figure 341. Variation of dime nsionless COP as a function of degree of subcooling in the condenser for various evaporator degree of superheat. Tcond=45oC, Tevap=5oC, Tamb=25oC, cond=0.75,comp=0.85, exp=0.85 Table 33. Hydrocarbons viewed as potential refrigerants MWTcrit, OC Pcrit, kPa crit kg/m3 Butane (R600) 58.12151.98 3796 227.84 Ethane (R170) 30.0732.18 4872 206.58 Isobutane (R600a) 58.12134.67 3640 224.35 Propane (R290) 44.196.675 4247 218.5 Propene (Propylene) (R1270) 42.0892.42 4664 223.39 0.98 1 1.02 1.04 0246810 Degree of subcooling, oCDimensionless COP 10 5 0Degree of superheat, oC PAGE 118 118 Figure 342. Variation of the refrigerati ng effect as a function of evaporating temp erature for various refrigerants at a cond ensing temperature of A) 25oC and B) 45oC for the ideal base cycle 0 50 100 150 200 250 300 350 400 5051 0 Evaporating Temperature, oCRefrigerating Effect, kJ/kg 0 50 100 150 200 250 300 350 50510 Evaporating Temperature, oC R134a R22 R12 Butane Isobutane Propane Proplyene A B PAGE 119 119 Figure 343. Variation of the ideal base cycle coefficient of performance as a function of ev aporating temperature for various refrigerants at a condens ing temperature of A) 25oC and B) 45oC 7 9 11 13 15 17 5051 0 Evaporating Temperature, oCCoefficient of Performance 3 4 5 6 7 50510 Evaporating Temperature, oC R134a R12 R22 Butane Isobutane Propane Proplyene A B PAGE 120 120 Figure 344. Variation of compressor work as a function of the evapor ating temperature at a condensing temperature of A) 25oC and B) 45oC for various refrigerants in an ideal base cycle 0 5 10 15 20 25 30 35 40 45 50510 Evaporating Temperature, oCCompressor Work, kJ/kg 15 25 35 45 55 65 50510 Evaporating Temperature, oC R134a R22 R12 Butane Isobutane Propane Proplyene A B PAGE 121 121 Figure 345. Variation of the increase of COP (when comparing the base cycle and th e expander cycle) as a function of the evaporating temperature for various refriger ants at a condensing temperature of A) 25oC and B) 45oC 6% 7% 8% 9% 10% 11% 12% 13% 14% 15% 50510 Evaporating Temperature, oC R134a R22 R12 Butane Isobutane Propane Proplyene 14% 16% 18% 20% 22% 24% 26% 28% 50510 Evaporating Temperature, oCIncrease in COP (base cycle and Expander cycle) A B PAGE 122 122 Figure 346. Variation of the decrease in ne twork (when comparing the base cycle and the expander cycle) as a function of the evaporating temperature for various refriger ants at a condensing temperature of a) 25oC and b) 45oC 5% 6% 7% 8% 9% 10% 11% 12% 13% 14% 50510 Evaporating Temperature, oCDecrease in the net work (between the base cycle and expander cycle) 10% 12% 14% 16% 18% 20% 22% 24% 50510 Evaporating Temperature, oC R134a R22 R12 Butane Isobutane Propane Proplyene A B PAGE 123 123 Figure 347. Variation of the increase in re frigerating effect (when comparing the base cycle and the expander cycle) as a func tion of the evaporating temperature for various refrig erants at a condensing temperature of a) 25oC and b) 45oC 0% 1% 2% 3% 4% 5% 6% 50510 Evaporating Temperature, oCIncrease in the refrigerating effect (when comparing base cycle and expander cycle) R134a R22 R12 Butane Isobutane Propane Propylene 0.0% 0.3% 0.5% 0.8% 1.0% 1.3% 1.5% 1.8% 50510 Evaporating Temperature, oCIncrease in the refrigerating effect (when comparing base cycle and expander cycle) A B PAGE 124 124 CHAPTER 4 MATHEMATICAL MODEL OF AN IDEAL ROTARYVANE EXPANDER Much literature has been reviewed in or der to formulate an accurate and rigorous analytic thermodynamic and fluid model of a ro taryvane expander. Mo st of the literature found deals with rotaryvane expanders us ed predominantly in hightemperature applications where the working fluid is va por (namely steam and R113) and is modeled using idealgas relations. This negates the ma ny additional complexities that arise due to the necessary formation of vapor from liqui d exiting the condenser in vapor compression cycles. These modeling complexities may include but are not limited to cavitational erosion, choking, issues dea ling with lubrication, and a po ssible increase of friction and internal leakage losses due to significant variations in the density and viscosity of the twophase working fluid. In order to accurately model a tw ophase rotaryvane expander, the studies conducted in the existing literature must be revisited and modified accordingly to predict such parameters as the work ing fluids pressure, temperature and mass variations as well as an overall estimate of power losses, volumetric efficiency, power output and torque of the rotaryvane expander. Literature Review of Modeling of Rotaryvane Expanders While literature dealing with modeling a nd design improvements of various types of compressors and expanders, such as heli cal screw, reciprocating piston, scroll, Wankelengines Badr et al. (1991a, 1991b, 1991c) and rotary piston are abundant, this review is confined to rotaryvane (or s lidingvane) type expanders and compressors, hence referred to as MVE and MVC, respec tively. Smith et al. (1990, 1992) introduced the principles, operation and testing of a nove l type compressor, the Groll rotaryvane compressor. They found a 19% and 15% increase in volumetric and adiabatic PAGE 125 125 efficiencies, respectively when compared to a conventional rotaryvane compressor. There have not been any st udies utilizing this as an expansion device. The positivedisplacement rotaryvane expa nder has been widely used for waste heat recovery in Rankine cycles. Badr et al. (1984) cited economics, ease of manufacturing and low maintenance as the most important parameters in the selection of a MVE as an expansion device. Among the investigators who developed mathematical models describing the geomet ry of rotaryvane type tu rbomachinery (compressors, expanders, pumps and airmotors) are Wo lgemuth and Olson (1971), Marsters and Ogbuefi (1972), Badr et al (1985a, 1985b), Somayajulu (1971), and BenBassat and Wolgemuth (1972). Mechanical friction in a MVE has been investigated by Beck et al. (1966), BenBassat and Wolgemuth (1972), Pe terson and McGahan ( 1972), Badr et al. (1986a), Robertson and Wolgemuth (1978), a nd Edwards and McDona ld (1972). Internal leakage losses in a MVE have been i nvestigated by Peters on and McGahan (1972), Jacazio et al. (1979), Badr et al. (198 5c), and Robertson and Wolgemuth (1978). All of the above studies either dealt with the expansion or compression of a working fluid (air, steam, a nd vapor) that could be modele d by the idealgas equation of state. The studies in question also dealt wi th rotaryvane type tu rbomachinery utilized as expanders in Rankine cycles as air motors or pumps. Tabl e 41 summarizes the type of application, working fluid, an alyses performed, and the type of losses accounted for. The extent and accuracy of their analys es is beyond the scope of this work. Model Development In order to accomplish this, five separate subroutines had to be constructed to accurately predict the aforementioned parameters. A simplified flow diagram of the main PAGE 126 126 computer program that has been developed and a brief descripti on, in subsequent sections, of the subroutines to be u tilized is presented in Figure 41. Thermophysical Model NISTs REFPROP 7.0s refrigerant prope rty subroutines are linked with the various models and are called whenever thermo physical data is requ ired. The capability to both use pure refrigerants and common re frigerant mixtures allows the use of REFPROPs property subroutines no matter the refrigerant. There is also the capability to use of a user defined and customized mixture. Geometric and Kinematic Model In order to model the perfor mance of a rotaryvane expander, the geometry of the expander and kinematics of the vanes must be accurately described mathematically. The basic geometrical and kinematic characteristics as a function of the angular displacement of the expanders rotor, are required to ev aluate the performance of the expander. The parameters needed include: Variation of the cell volumes Volume expansion ratio, rv=V2/V1 (Figure 42) Variations of the protrusions of th e vanes outside their rotors slots Vanes sliding velocity Vanes accelerations A review of the literature reveals that ma ny different models have been considered (Table 41). A primary difference among th e models is accounting for the vane thickness. Many researchers have assumed an idealized vane thickness of zero when calculating the cell volume. For the purpose of this study, the expander is assumed to have a circular statorcylinder and the thickness of the vanes is ta ken into account initia lly. It can be shown PAGE 127 127 from Figure 42 that a circul ar stator cylinder may be m odeled as having two arcs (2seal and seal) one of which is a sealing arc. The geometrical input parameters to the model and nomenclature used throughout this section are listed in Table 42 and are shown on a schematic of a circular expander in Figure 42. It should be noted that if the sealing arc is symmetric a bout the base line, that =180o and RS()=180o. Neglecting the thickness of the vanes and assuming that the vanes are in continuous contact with the stator cylinde r, the ideal volume of the expa nders cell as a function of angular displacement may be written as cvcvcvVAAL (41) where Acv() and Acv() are the areas enclosed between the stator and rotor cylinders and the datum and the leading and trailing va nes respectively. The area functions have been calculated using the equations and nume rical procedure presented in Badr et al. (1985). The actual volume of the expanders cel ls differs by accounting for the volume of the extended portions of the leading and tra iling vanes outside of the rotors slots. In order to calculate the kinematics of the vanes and the actual volume of the expanders cell, the protrusions of the vanes from the rotors slots must be computed. The vanes are assumed to be rigid. R() is defined as the radius of the statorcylinder to the center of the rotor as a function of angular displacement. For a circular statorcylinder this quantity may be simp lified and expressed as 2222cos2cossinRRRereere (42) where is defined as the angle between the arcs center and that of the rotor. The vanes protrusion from the slot ma y then be defined as PAGE 128 128 R X Rr (43) The sliding velocity and the acceleration of the vanes may be determined by differentiating Equation (43) with respect to time once a nd twice, respectively. A FORTRAN subroutine has been de veloped to calculate the geom etrical characteristics of a circular rotaryvane expander for a given set of input parameters. Thermodynamic Model To model the performance characteristics of an expander, the principles of conservation of mass and energy in each of th e expanders cells must be used. This will allow the prediction of the pressure, temperat ure and mass variations of the working fluid in the cells as a function of the rotors angul ar displacement. This will require accurate calculation of both the variati on of the cell volume and the thermophysical properties from the geometric and thermophysical m odels, respectively. The basic geometrical relationships modeled th en helped describe: Variation of the cell volumes Volume expansion ratio Inlet and exhaust por t area variations As mentioned earlier, in order to model the thermodyna mic and throttling characteristics of an expander, the principles of conservation of ma ss and energy in each of the expanders cells must be used. Thes e would allow the prediction of the pressure, temperature and mass variations of the worki ng fluid in the cells as a function of the rotors angular displacement. A computer program has been coded to calculate the mass, pressure and temperature variations in the expanders charging, expansion, and exhaust stages. Figure 42 shows the various stages of flow of a working fluid thr ough the rotaryv ane expander. PAGE 129 129 The following characteristics are calculated once the inlet state to the expander is defined and the mass, pressure and temperat ure variations in th e expander are found: Volumetric efficiency: an indicator of how well the expanders cell was filled during the charging process Throttling power factor: a ratio of the i ndicated power of the expander with only throttling losses in ports accounted for and the indicated power of an ideal expander Throttling Efficiency: A ratio of the sp ecific work of the expander with only throttling losses accounted for and the specific work of an ideal expander The throttling losses in the intake and e xhaust ports are only pr esented here briefly but will be discussed and modeled in the subsequent chapter. Charging Process The charging process takes place at angular displacements of 0in The temperature of the fluid entering the expande r can be determined from the degree of subcooling the fluid undergoes in the condenser. The saturati on pressure corresponding to the saturation temperature of the condenser, the state of the fluid entering the expander can also be determined. This state is denoted by the subscript (int). The mass flowrate of the working fluid th at fills the cavity, assuming steady flow and ignoring changes in potential energy, can be written as int int int) ( ) (V A C md in (44) where the coefficient of discharge is assumed to be unity initially and will be determined by experimental data. The inle t throat area varies as a f unction of angular displacement and was found to obey the linear approximati on that Wolgemuth and Olson (1971) have suggested. A typical linear appr oximation of the inle t throat variation is shown in Figure 43. PAGE 130 130 The expression for the amount of mass c ontained in the expander cell at any angular displacement is the following d m m min cv cv 0) ( ) 0 ( ) ( (45) The first law of thermodynamics can be written for the process as follows (taking heat into the system and work done by the system as positive) intint cv bdE QWmh dt (46) Assuming the changes in kinetic ener gy and potential energy are neglected, Ecv=dUcv. The pressure within the control volume is also assumed to be uniform. Multiplying by dt and neglecting friction, inte rnal leakage losses and heat transfer, Equation (46) becomes 121inint()mtUPVVh (47) Solving for the internal energy of the refrig erant at the new time step, State 2, we find 11121inint 2 2()mtmuPVVh u m (48) The density of the refrigerant at the ne w time step, State 2, is calculated as 2 2 2V m (49) The charging process is assumed to be a constant pressure process (P1=P2=Pint). This conclusion is supported by much of the literature including Ta niguchi et al. (1983) and Baek (2002). The mass in the control volume at State 2 is thus an unknown. In this case, the first law of thermodynamics can be written as 221112121int()() UmumupVVmmh (410) PAGE 131 131 The mass at State 2 can be expressed however as 2 2 2V m (411) Substituting Equation (411) into Equation (410) we get 22211121221int()() VumupVVVmh (412) where 2 and u2 are the unknowns. Neglecting temperat ure gradients within the control volume, these two unknowns may be determin ed by iterating on the temperature of the control volume that corresponds to the known pressure, P2, and simultaneously satisfies the conservation of energy statement, Equa tion (412). The thermodynamic state of the control volume at the new time step or angular displacement has hence been fully defined and this procedure is carried out until the cutoff angle ( = in+ ). Expansion Process During the expansion process, inex the mass in the control volume, mcv, stays constant after the cutoff anglein cut where in is the spread of the intake port and is the angle between successive vanes (e.g. =45o for an eightvane expander). Assuming internal leakage losses are neg ligible, the mass in the control volume, mcv, is assumed to be constant throughout the expansion process. If pressure gradients within the control volume, changes in kine tic and potential ener gy, friction and heat transfer are also neglected, the process be tween the current and new time step may be assumed to be isentropic and hence 21ss (413) The density at the new time step may be determined from 2 2V mcv (414) PAGE 132 132 The thermodynamic properties at the new tim e step, namely temperature, pressure, and quality, can be calculated from Equati ons (413) and (414) with the use of REFPROP 7.0. This process is repeated until the end of the e xpansion process at a predetermined exhaust angle of ex. Exhaust process The exhaust process occurs at an exhaust angle exendout where out is the spread of the exhaust port and is the angle between consecutive vanes. During the exhaust process, the mass flow rate of the working fluid discharged from the control volume as a function of a ngular displacement can be determined from the following equation ,()()exdexcvexexmCAV (415) where cv is the density of the working fluid in the control volume at the current time step. The discharge coefficient, Cd,ex, is an empirically determined constant that takes into account exit port losses. Here, the discharge coefficient is assumed to be unity. The variation of the exit throat area, exA can be seen to follow the linear approximation proposed by Wolgemuth and Ol son (1971) in Figure 44. The amount of mass contained in the cont rol volume at any angular displacement can then be expressed as d m m mexex ex cv cv ) ( ) ( ) ( (416) where ex is the angle at the end of the expansion process. The first law of thermodynamics can be written for the process as follows PAGE 133 133 cv bexexdE QWmh dt (417) Neglecting changes in kinetic a nd potential energy leads to Ecv=Ucv. The exhaust process is assumed to occu r at constant pressure cvexexPP and in an quasiequilibrium manner. Neglecting friction, intern al leakage losses and heat transfer from the ambient, Equation (417) reduces to 21()exexexUPVVmh (418) Applying the same solution methodology as in the charging process, Equation (418) simplifies to 22211212211()()exVumuPVVVmh (419) where 2 and u2 are the unknowns. Neglecting temperat ure gradients within the control volume, these two unknowns may be determin ed by iterating on the temperature of the control volume that corresponds to the known pressure, P2, and simultaneously satisfies the conservation of energy statement, Equa tion (419). The thermodynamic state of the control volume at the new time step or angular displacement has hence been fully defined. Ideal Expander Evaluation For a given set of operating temperatures in a refrigeration system, the state of the refrigerant entering and leaving the expander may be determined. The resultant process volume ratio is defined as 3 evapin vpv r v (420) where v3 is the specific volume of the fluid at the condenser exit. The refrigerant may be a saturated or subcooled liquid at this state. This process volume ratio is expected to be PAGE 134 134 smaller when the refrigerant leaving the condenser is subcooled. The builtin (or geometric) volume ratio of the expander may be expressed as ex vbin inv r v (421) It should be noted that the terms built in and geometric volume ratios are used interchangeably. If internal leakage losses ar e neglected, this parameter reduces to the ratio of the expanders ce ll volumes since at both ex and in+ the mass in the cell volume is constant. If the builtin volume ratio is less than, identical to or greater than the process volume ratio then underexpansion, ideal e xpansion and over expansion will occur, respectively. The expander s hould not only match (or be fairly similar to) the process expansion ratio for typical system operat ing conditions but should also minimize the amount of wasted power rec overy due to pressure lo sses incurred during underexpansion. In the case of overexpansion, the higher pressure of the downstream reservoir may result in refrigerant flowing back into the expander via the exhaust port further complicating the actual exhaust process. Overexpansion is not accounted for in this study. Figure 45 illustrates the three possible scenarios depending on the builtin and process volume ratios. The appropriate select ion of the dimensions of the e xpander is critical to ensuring adequate operation. In general, turbomach ines are designed such that the volumetric flowrate of the working fluid is identical to the volumetric displacement of the device. For the case of an expansion device employed in a refrigeration system this equality may be expressed as ,60drefininVmv (422) PAGE 135 135 where is the rotational speed of the expander in RPM and dVis the volumetric displacement per revolution of the expansion device. The righthand side of Equation (422) represents the volumetric flowrate of refrigerant in m3/s that enters the expander after leaving the condenser in either a satura ted or subcooled liquid state. The rotational speed is the primary design variable for gi ven operating conditions and geometry of the expander. As the rotational speed of the expa nder increases, frictional losses and internal leakage typically increase a nd decrease, respectively. An optimum operating condition exists where the product of the disp lacement volume of the expander in m3/rev and its rotational speed minimize friction, leakage losses and the manufact uring cost of the expander. In order to calculate the torque and powe r developed by the expander, the pressure forces acting on the vanes must be computed. If the pressure forces are assumed to act at the midway point of the vanes calculated pr otrusion from the rotor slots and no internal leakage losses are assumed past the vane tips, the following expression for the torque developed by one vane at any angular displacement may be written 2v vvcvcvRX TXLPPr (423) If frictional losses are also assumed negligib le, the average of the sum of the torque developed by the expander at any angular displacement multiplied by the rotational speed is the power that may be extracted from the expander. The resultant power as a function of angular displacement may be expressed as 2 21 1221 exp 0()()inex inexin cvexPVV muuPVV W ttt (424) PAGE 136 136 The appropriate selection of the geometry and rotational speed of the expander ultimately depends on the application. Parameters of interest for typical operating conditions for a basic and modified refrigera tion system are tabulated in Table 43. The apparent advantages of employing an expansion device include reduction in mass flowrate and process volume ratio, incr ease in the system COP, refrigerating efficiency and refrigerating effect. The netwo rk required by the system also decreases if the expander work is assumed to be ideally coupled to the comp ressor shaft. As the efficiency of the expansion device increases, it can be seen that further decreases in the mass flowrate and process volume ratio ar e obtained. Similar trends for various operating conditions, component efficiencies, degrees of su perheating and subcooling are expected. In order to determine the work extracti on potential of an expander with a known geometry, an alternative numerical solution pr ocedure to that detailed in the charging, expansion and exhaust sections must be ut ilized. The charging and exhaust processes were assumed to be isobaric and hence th e mass flowrate of refrigerant is unknown. There exists, however, a unique value of the incoming and leaving refrigerant mass flowrate at which the power extr action is optimum. The mass flow rate is hence iterated upon in order to satisfy Equations (412) and (419). Cerpnalkovski (1991) suggested typical va lues of aspect ratio (rR/L) of a rotaryvane compressor of 0.50.8. For the purpose of this study the aspect ratio was assumed to be 0.46. The eccentricity of the rotor and stator cylinders was also assumed to be 2.6 mm. The dimensions of the expander are assumed to be 28 mm, 30.6 mm and 12.7 mm for the PAGE 137 137 rotor radius, statorcylinder radius and the axial length of the expander respectively. The sealing arc is assumed to have an arclength of seal=40o. The most important geometrical design parameter, which ensures adequate size and performance of any expansion device, is th e builtin volume ratio. Figure 46 shows the variation of the builtin volume ratio as a function of the inta ke angle for various numbers of vanes. The intake angle is found to be the most critical parameter that influences the performance of a rotaryvane type expande r. For all intake angles analyzed, the thermodynamic performance and builtin volume ratio are maximum when the exhaust angle is ex=189o. The volume ratio is found to decrea se as the intake angle increases independent of the expanders number of vanes. As the number of vanes in the expander increases this decrease is found to increas e dramatically. The increase in the number vanes may also be limited by the dynamics a nd mechanical strength of the rotor and the added frictional and internal leakage losses that may result. The e xpanders intake angle should hence be designed to optimize both the thermodynamic and geometrical performance. A single value of the intake angle may not optimize both simultaneously, however. Application dependent optimization is thus necessary. Although smaller intake angles result in larger builtin volume ratios, higher throttling losses are typically associated with them. The expanders builtin volume ratio can be seen to decrease by 40%, 58.3% and 67% for the entire range of in take angles investigated for 4,8 and 12 vane expanders, respectively. Medi an values of the intake angle ( in=15o) and number of vanes (N=8) have been selected in order to avoid the aforementioned complications at which the volume ratio is rv,b=5.4305. PAGE 138 138 The displacement volume of a circular ro taryvane expander may be computed for any given set of input parameters detailed in Table 43. The control volume analyzed is defined as the volume bounded by the statorcyl inder, rotor, leadi ng and trailing vanes and the two axial endplates. Fi gure 47 illustrates the ideal cell volume variation as a function of angular displacement for different numbers of vanes. The displacement volume per revolution is the cutoff volume multiplied by the number of vanes. Figure 48 shows the difference between the ideal and actual volume. By accounting for the thickness of the vanes, tv=4.2 mm, a slight shift in the volume curve is observed. This results in a deviation by as much as 89% and by as little as 1% at initial and at larger angular displacements. It can also be seen from Figure 48 that the maximum ideal and actual volume occurs at =184o and =180o respectively. The condensing and evaporati ng pressures corresponding to 50oC and 0oC condensing and evaporating temperatures ar e 1.942 and 0.498 MPa, respectively. This corresponds to a process volum e ratio of 14.74 if the refrigerant is assumed to be expanded isentropically. Figures 49 and 410 illust rate the variation of the pressure within the expander as a func tion of the volume within the expander for various intake angles and numbers of vanes, respectively. Th e pressure is found to be greater than the desired exhaust pressure primar ily because the builtin volume ratio is not equivalent to the process volume ratio. From Figure 49, it can be shown that builtin volume ratios of 8.16, 6.6 and 5.43 corresponding to intake angles of 5o, 10o and 15o, respectively, correspond, to exhaust pressures 15%, 32.2% and 40% higher than the desired exhaust pressure. Figure 410, illustrates how the numbe r of vanes affects th e pressure variation in an expander for a given intake angle. It can be shown that bu iltin volume ratios of PAGE 139 139 4.083, 5.43 and 6.6 corresponding to 6, 8 and 10 vane expanders result in 53%, 40% and 26% higher exhaust pressures, respectively. These differences are primarily due to inadequate builtin volume ratios of th e expander and result in less desirable thermodynamic performance. Unless a throttl e valve or another means of expanding the discharging fluid to the eva porating pressure is used, fl ashing and/or other losses are imminent. For the purpose of this ideal anal ysis the losses due to underexpansion are not included in the models developed and it is a ssumed that a throttle valve further expands any underexpanded refrigerant to the evaporator pressure. Independent of the builtin volume ratio, the optimum performance of an expander is expected to occur when the mass flow of the working fluid is maximum. The maximum mass flowrate will likely have to be greater if the builtin volume ratio of the expander is inadequate. Accurate models fo r the mass flowrate of an actual expander may be developed in which inlet area, exhaust area, velocity and dens ity variations as a function of angular displacement are modele d. Figure 411 shows the variation of the mass trapped in the expanders control volume as a function of angular displacement for various intake angles. It can be seen that as the intake angle increases, the greater the amount of mass in the control vo lume during the expansion pro cess. This results from the fact that the expanders cutoff is delayed. These delays in cutoff are represented as lines (a), (b) and (c) respectively. It is found that the mass in the control volume during expansion is 50% and 28% hi gher for intake angles of =25o and =10o, respectively, when compared with that of =5o. Figures 412 and 413 show the variati on of power extracted during the process expansion as a function of angular displacemen t for various intake angles and different PAGE 140 140 numbers of vanes. Figure 412 shows that the maximum power extracted prior to the exhaust process is 1440 W, 742 W and 534 W for 6, 8 and 10 vane expanders, respectively. At the conclusion of the exha ust process, the net power output from the expander is 355 W, 305 W and 257 W corresponding to 6, 8 and 10 vane expanders respectively. It can also be seen from Figur e 413 that as the intake angle increases the maximum power extracted prior to the exha ust process is 611 W, 690 W, 742 W and 794 W corresponding to in take angles of 5o, 10o, 15o and 20o, respectively. At the conclusion of the exhaust process, the net power output fr om the expander can be seen to be 309 W, 307 W, 305 W and 297 W correspondi ng to intake angles of 5o, 10o, 15o and 20o respectively. Figure 414 show s the variation of the power extracted as a function of volume for a particular set of input paramete rs. The same general trends of Figures 412 and 413 is observed. Theoretical simulation models have been developed to analyze and evaluate the geometric and thermodynamic performance of a circular rotaryvane expander. The following conclusions can be made: The builtin volume ratio can be seen to decrease by 40%, 58.3% and 67% for the entire range of intake angles investigated for 4,8 and 12 vane expanders respectively. The increase of the numbe r vanes may be limited by the dynamics and mechanical strength of the rotor and the added friction and internal leakage that may result. Lower intake angles result in larger builtin volu me ratios but higher throttling losses are typically associated with them. As the spread of the intake angle decreases and the number of vanes increases, hence an increase in the builtin volume ratio, the resultant exhaust pressure is found to reach the evaporating pressure. Th ese differences are primarily due to the inadequate builtin volume ratio of th e expander and result in less desirable thermodynamic performance. Unless a throttle valve or another means of expanding the exhaust fluid down to the evaporating pressure is used, flashing a nd/or other losses are imminent when the refrigerant is underexpanded. PAGE 141 141 As the number of vanes increases, the net power output of the expander decreases. For the cases investigated, as much as 75% of the power extracted prior to the exhaust process is consumed by the exha ust process. Compared to a 10vane expander the net work output of a 6vane expander is found to be greater by as much as 27% As the intake angle increases, the maxi mum power extracted prior to the exhaust process increases. At the conclusion of th e exhaust process, the net power output from the expander is found to deviate only 2% from the mean. The thermodynamic model developed in this section was ideal in its assumptions and analysis. It did not take into account losses that may ar ise due to thro ttling in the intake and exhaust ports, twophase internal leakage, friction, heat transfer, recompression or irreversible losses due to overor underexpansion caused by inadequate expander sizing. Chapter 5 details the th eory and presents models of those aforementioned loss mechanisms. Once describe d, the models for these loss mechanisms will modify the thermodynamic model develope d in this chapter to provide an accurate estimate of the expanders detailed and overall performance. PAGE 142 142 Figure 41. Flow diagram of the main computer program developed Geometric and Kinematic Model Thermophysical Model Friction Model Internal Leakage Model Throttling Model Expander Model Inputs: (from Vapor Compression System Model) Pressure Temperature Outputs: (to Vapor Compression System Model) Pressure Temperature Power Output Volumetric Efficiency Tor q ue PAGE 143 143Table 41. Summary of rotaryvane literature Analysis No. Investigator Application Working Fluid Eq of StateGeometrical Thermodynamic Friction Internal Leakage HeatTransfer Lubrication 1 Peterson and McGahan (1972) Compressor Air Idealgas x x x x 2 Badr et al. (1985a) Expander in ORC General x 3 Badr et al. (1985b) Expander in ORC R113 Idealgas x 4 Badr et al. (1985c) Expander in ORC R113 Idealgas x 5 Badr et al. (1986a) Expander in ORC R113 Idealgas x 6 Badr et al. (1986b) Expander in ORC R113 Idealgas x 7 Edwards and McDonald (1972) Expander in ROVACAir Idealgas x 8 Robertson and Wolgemuth (1978) Expander in RC Steam Idealgas x x x 9 Beck et al. (1966) Compressor in VC R12 vapor na x 10 Marsters and Ogbuefi (1972) Air Motor Air Idealgas x x 11 Somayajulu (1971) Pump Air Idealgas x x x 12 BenBassat and Wolgemuth (1972)2stage Exp in RC Steam K & K* x x x 13 Wolgemuth and Olson (1971) Expander in RC Steam K & K* x x x 14 Jacazio et al. (1979) Air Motor Air Idealgas x x 15 Bransford and Stein (1960) Compressor in VC Air and R12 Idealgas x x 16 Robertson and Wolgemuth (1975) Expander in RC Steam Idealgas x x x x x 17 Barszcz, Z. (1980) Air Motor Air General x x VC: Vapor Compression refrigeration system RC: Rankine Cycle ORC: Organic Rankine Cycle ROVAC: ROtary Vane Air refrigeration Cycle *Keenan and Keyes equation of state for steam PAGE 144 144 Figure 42. Schematic of a generally orie nted circular rotaryvane expander with 8 vanes described by two circular arcs Sealing arc Trailing vane STATOR Leading vane ROTOR in ex OS OR e rRV2 V1 rS seal RS( ) R( ) Charging Process 0< < + Expansion Process + ex Exhaust Process ex< <2 Base Line =0 PAGE 145 145Table 42. Geometrical input parameters Input Parameter Symbol Rotor radius, m rR Eccentricity, m e Angle between rotor and statorcylinder centers Stator cylinder radius, m rS=rR+e Axial length of expander, m L=AR.rR Number of vanes N Angle between successive vanes, deg =360o/N Thickness of vanes, m tv Inlet port arclength, deg in Exhaust port arclength, deg ex Arclength of sealing arc, deg seal PAGE 146 146 Figure 43. Variation of the inlet throat area with respect to angular displacement Figure 44. Variation of the exit throat area as a function of angular displacement for an 8vane circular MVE 0 0.0005 0.001 0.0015 0.002 0.0025 0.003 020406080100 Angular Displacement, degInlet Throat Area, m2 0 0.0005 0.001 0.0015 0.002 0.0025 0.003 150200250300350400 Angular Displacement, degExit Throat Area, m2 PAGE 147 147 Figure 45. Pressure variation as a function of volume in an ideal expander for the cases of ideal, over and under expansion. + exP Pin buit v process vr r, P Vint ex in in Ideal Expansion UnderExpansion Over Expansion in buit v process vr r, in buit v process vr r, + exP Pin buit v process vr r, P Vint ex in in Ideal Expansion UnderExpansion Over Expansion in buit v process vr r, in buit v process vr r, + exP Pin buit v process vr r, P Vint ex in in Ideal Expansion UnderExpansion Over Expansion in buit v process vr r, in buit v process vr r, exP Pin buit v process vr r, P Vint ex in in Ideal Expansion UnderExpansion Over Expansion in buit v process vr r, in buit v process vr r, P Pin buit v process vr r, P Vint ex in in Ideal Expansion UnderExpansion Over Expansion in buit v process vr r, in buit v process vr r, in buit v process vr r, P Vint ex in in Ideal Expansion UnderExpansion Over Expansion in buit v process vr r, in buit v process vr r, PAGE 148 148 Table 43. Typical operating conditions for a basic and modified 2 ton system *R22, 2 ton cooling capacity, Tcond=50oC, Tevap=0oC, c=0.85, no superheat, no subcooling, pressure losses in lines and components neglected Expander Isenthalpic Expansion exp=0.45 exp=0.85 Isentropic Expansion ,g/s 49.6 48.61 47.77 47.5 v3, m3/kg 0.000924 0.000924 0.000924 0.000924 rv,p 16.3 15.6 14.97 14.74 COP 3.52 3.87 4.23 4.38 ref, % 64.4 70.8 77.4 80.1 wexp, kJ/kg 2.89 5.46 6.42 wnet, kJ/kg 40.3 37.4 34.8 33.8 qeva p kJ/kg 141.1 144.7 147.3 148.2 refm PAGE 149 149 Figure 46. Variation of builti n volume ratio as a function of intake angle for different numbers of vanes Figure 47. Variation of ideal volume as a function of angular displacement for different numbers of vanes 0.0E+00 5.0E07 1.0E06 1.5E06 2.0E06 2.5E06 3.0E06 3.5E06060120180240300360 Angular Displacement degIdeal Volume, m3 N=4 N=6 N=12 N=8 N=10 A R=0.46 rR=27.9 mm e=2.7 mm in=15oout=189o 0 2 4 6 8 10 1015202530 Intake Angle in, degBuilin Volume Ratio rv,b N=4 N=6 N=8 N=10 N=12 PAGE 150 150 Figure 48. Variation of ideal and actual volumes as a function of angular displacement Figure 49. Variation of pre ssure as a function of volume for various intake angles 0 500 1000 1500 2000 25000.0E+005.0E071.0E061.5E062.0E06Volume, m3Pressure, kPa A R=0.46 rR=27.9 mm e=2.7 mm N=8 out=189oPinletPexhaust} Losses}} in=5oin=10o in=15o 0.0E+00 4.0E07 8.0E07 1.2E06 1.6E06 2.0E060100200300400 Angular Displacement degVolume, m3 Ideal ActualAR=0.46 rR=27.9 mm e=2.7 mm N=8 in=15oout=189o PAGE 151 151 Figure 410. Variation of pressu re as a function of volume fo r different numbers of vanes Figure 411. Variation of mass within the expanders cell volume as a function of angular displacement for various intake angles 0 500 1000 1500 2000 2500 0.0E+005.0E071.0E061.5E062.0E062.5E06 Volume, m3Pressure, kPaPinletAR=0.46 rR=27.9 mm e=2.7 mm in=15oout=189oN=10 N=6 N=8 0.0E+00 1.0E04 2.0E04 3.0E04 4.0E040100200300 Angular Displacement degmcv( ), kgin=25oin=5oin=10o Expansion Exhaust Intake (a) (b) (c) AR=0.46 rR=27.9 mm e=2.7 mm N =8 =58 rpm out=189o PAGE 152 152 Figure 412. Variation of power as a func tion of angular displacement for different numbers of vanes Figure 413. Variation of power as a function of angular displacemen t for various intake angles 0 0.2 0.4 0.6 0.8 1 1.2 0120240360 Angular Displacement ,degPower, kWN=10 N=8 N=6 Net Power Output AR=0.46 rR=27.9 mm e=2.7 mm =58 rpm in=15o out=189o 0 0.2 0.4 0.6 0.8 1 0120240360 Angular Displacement degPower, kWin=20o A R=0.46 rR=27.9 mm e=2.7 mm N=8 =58 rpm out=189oin=5oin=10o in=15o PAGE 153 153 Figure 414. Variation of power as a function of volume 0 0.2 0.4 0.6 0.8 0.0E+005.0E071.0E061.5E062.0E06Volume, m3Power, kW Intake and Expansion Exhaust Net Work Output AR=0.46 rR=27.9 mm e=2.7 mm N=8 =58 rpm in=15oout=189o PAGE 154 154 CHAPTER 5 PRIMARY AND SECONDARY LOSS MECH ANISMS IN ROTARYVANE TWOPHASE REFRIGERATING EXPANDERS All turbomachinery operate with energy and mass losses. These losses may be attributed to twophase internal leakage, friction, throttling losses in the intake and exhaust ports, recompression in the expander cavity and overor underexpansion due to inadequate sizing of the geometric volume ratio. Primary Loss Mechanisms The aim of this chapter is to develop ma thematical models that would account for the primary loss mechanisms of internal leak age and friction. The size of a rotaryvane expander is of primary interest due to th e influence it has on the magnitude of loss mechanisms present. While rotaryvane comp ressors are typically very efficient, at smaller sizes, the effect of losses such as in ternal leakage becomes much larger. In rotaryvane expanders of smaller sizes both the volumetric and adiabatic efficiencies are expected to be smaller. Depending on the ope rational and geometrical parameters of the expander, laminar and viscous twophase le akage flow within the expander may be present. Singlephase leakage models availabl e in the literature must be revisited and modified accordingly. A dynamic frictional model for the expander must also be developed for ideal operation (i.e. no intern al leakage) and modified to account for internal leakage accordingly. A comprehens ive componentlevel model of inherent friction and internal leakage losses in a twopha se circular rotaryvan e expander used in a vapor compression refrigeration system is presented. The model establishes the efficiency and performance of the expander as a func tion of geometric and fluid parameters. Accurate modeling and prediction of frictiona l and internal leakag e losses is vital to PAGE 155 155 being able to accurately estimate the effici ency, rotational speed, and the torque and power produced by the expander. Internal Leakage Paths and Clearances The clearances between the rotor and stator cylinders, endplates and vanes provide the necessary seals of the expander cavity. Ca ution must be exercised when designing an expanders assembly clearances. Depending on the operating conditions and geometric volume ratio, large temperature gradients may al so lead to thermal deformations of these materials. The clearances must be minimized for each application to ensure control of internal leakage losses yet re compression of liquid may lead to inadequate operation or liquid locking. The various leakage path s are tabulated in Table 51. The volumetric efficiency of an expande r may be larger than unity due to significant increases in the consumption of the working fluid. This significant increase is primarily a result of internal leakage losses. The magnitude and sources of internal leakage must be identified and minimized. The magnitude and sources of internal leakage is significantly dependent upon the way by which the working fl uid is introduced into the expanders cavity. Figure 51 illustrates th e difference between th e conventional (a) and modified (b) methods through which the fluid is introduced into the expanders cavity. The conventional intake port is machined directly into the statorcylinder. The modified intake is comprised of slots machin ed in both endplates after which the fluid is introduced into the expanders cavity via a slot machined in to the rotor at a specific angle from the slot. Upon the completion of the geometric, kinematic and thermodynamic models, the predicted pressure and quality of the refrig erant in the expanders control volume are used to calculate the leakage of refrigerant through the various leakage flow paths. In PAGE 156 156 order to model internal leakage between cont rol volumes, the flow areas of the leakage paths, Aleak, must be estimated. The mass flowrate of internal leakage can be written in general form as leakdleakleakleakmCAu (51) where Cd is an empirical discharge coefficient. The density and velocity of the leakage are a function of the angular displaceme nt at which the leakage occurs and the thermodynamic state of the fluid. Of primary in terest is the computa tion of the velocity. The net mass flow leaked into the cavity form ed by the adjacent vanes, stator and rotor cylinders (see Figure 51) can be computed as leakleakleakmmm (52) Leakage from Path (6) is neglected. It s hould be noted that if the sealing arc is symmetric about the base line then =180o and RS( )=rS. Types of TwoPhase Leakage Losses The majority of internal leakage models in turbomachinery presented in recent literature are developed for singlephase comp ressible flow. The friction associated with incompressible leakage losses through a duct or leakage path of constant crosssectional area affects only pressure in the direction of the flow. The velocity of the working fluid remains constant. According to Oothusizen ( 1997), in compressible flow, friction affects all of the flow variables, i.e., the changes in pressure cause changes in density which lead to changes in velocity For twophase flow th is also necessitates vaporization of liquid, which alters the density of the working fluid significantly. Depending on the operational and geometrical parameters of the expander, turbulent twophase leak age flow within the expander may be present. PAGE 157 157 In the case of twophase viscous leakage losses, the twophase mixture is assumed to be homogenous in nature. The idealizatio ns adopted under this fairly common model include assuming that the vapor and liquid velocities are equal. The overall twophase flow is also assumed to behave like a single phase, uniformly mixed, having fluid properties whose values are, in some sense, mean values for the flow according to Carey (1992). According to Levy (1999), assuming hom ogenous flow also allows the ability to apply all available singlephase flow analys es and empirical correlations The density of the homogenous twophase mixture is computed as 11 g f x x (53) The calculation of other necessa ry properties for the twophase mixture, such as the specific heats and viscosity, can be very tr oublesome. Many different formulations have been proposed throughout th e literature. Among them, 1 f g x x (54) 11 g f x x (55) 1 g f gfxx (56) For example, a twophase mixture of water at P=500 kPa and x=0.2 yields a viscosity of 146.09, 53.52 and 15.968 Pa.s from Equations (54), (55) and (56), respectively. According to Carey (1992), E quation (55) is the most comm on. Properties can also be computed by utilizing the concept of the homogenous void fraction PAGE 158 158 1f f gx xx (57) and hence the dynamic viscosity can be computed from 1fg This method will be used since the computed value is identi cal to that obtained from Equation (56). In the same manner the specific heats and thermal conductivity can be computed. Viscous effects must be accounted for when computing the pressure drop and mass flowrate through radial clearances, e.g. flow through minimum clearance. These channels are typically long a nd wide when compared to the height of the channel. Viscous effects may be neglected when deali ng with nozzles or short ducts. The axial leakage flow between the vanes and the endplates is an example where viscous effects may be neglected. The flow of the twophase compressible leakage, accounting for friction, can be modeled as adiabatic Fannoflow. Figure 52 shows a schematic of a typical leakage path. The dimensions of the leakage path, crosssectiona l area and length, are known and depend on the leakage path under consideration. The exit, (e), could be choked depending on the difference between the pressure of the re servoir and back pressure at local angles and + respectively. Darby (2001) concludes that the ratio of the sonic velocity in a homogenous mixture to that in a gas alone is much smaller than un ity. In this case choking can occur in a twophase mixture at a significan tly higher downstream pressure. This corresponds to both a lower pressure drop and mass flux. The flow is choked when the velocity at the exit plane is equal to the speed of sound. For a nonflashing liquid and an idea l gas mixture, the maximum mass flowrate PAGE 159 159 in the channel can be computed. The isen tropic speed of sound for a homogenous twophase mixture can be computed as s P a (58) The governing equations and the discretized form of those equations are presented in Table 52 and are derived from first princi ples and describe adia batic Fanno flow from a reservoir. It should be noted that the vol ume of the leakage channel is V=Hwl and the mass flowrate through the channel is eemuHw The Darcy friction factor, f is assumed constant over the length of the leakage channe l. This is a fairly reasonable assumption since the flow is typically found to be fully developed over a majority of the channel length. For Reynolds numbers in the lower ra nge of the turbulent region, the modified Blasius correlation is 0.250.33ReHf (59) where the Reynolds number is defined as Re H eeuHv This correlation has been shown to be in good agreement with various experiments throughout the literature. The momentum equation can ther efore be expressed by 1.75 2 1 0.751.250.165e eee elu PPu vH (510) The methodology used to solve for adiabati c Fannoflow through a leakage path is an iterative procedure. The state of inle t to the channel is known. Depending on the leakage path and the state of the refrigerant, the flow may be of an incompressible liquid or a compressible twophase refrigerant. The unknowns, in Equation (510), that remain PAGE 160 160 are ue, m Pe and e. The iterative procedure calls for an initial guess at the exit plane of the channel where the flow is assumed to be choked. An initial guess of the pressure at the exit plane may correspond to the average pres sure that exists in the adjacent expander cell. The flow is assumed to be isenthalpic or isochoric in the case of twophase or liquid flow, respectively. In the case of the twopha se flow the quality is known. Based on the initial guesses, the speed of sound can be cal culated. If the flow is choked at the exit plane, i.e ue=a, then P is iterated upon until Equations (55), (58) and (510) are satisfied simultaneously. If the flow is viscous and the exit plane is unchoked, the average velocity of the leakage can be determined by solving generalized Couette fl ow, see Figure 53, the flow is driven by both the shear of a moving wall a nd a given pressure differential. Solving the momentum equation and applying the nosl ip and moving wall boundary conditions the velocity distribution is 21 ()()mdPr uyyyy dx (511) The mean velocity between the plates is defined as 01m yuuydy (512) and after integration is found to be 2212m mrdP u dx (513) If the flow in the leakage path can be modeled as isentropic flow through a nozzle whose throat is choked then the initial guess used to evaluate the sonic velocity is 1 i e P P and 1 e s s The density is then calculated. The pressure and density at isentropic PAGE 161 161 conditions, at the exit plane, are iterated upon accordingly until the computed speed of sound is identical to the relationship obtained from the energy equation, 12()eeuhh In the case that the isentropic flow is unchoked, the exit plane pr essure is equal to the backpressure, Pe=Pb and se=s1. The thermodynamic state at the exit plane can then be established and the velocity at the exit can be determined by Equation (58). Axial Clearance Between Rotor and End Plates The flow of the fluid between the rotor and endplates can be modeled as that of a fluid flowing in a narrow gap between a disc which rotates within a chamber of finite dimensions. The boundary conditions imposed on the periphery of the rotating disk are nonaxisymmetric in nature due to the pressure distribution of the fluid in the expanders cavity. The effects of the vanes and their slots are neglected. The characteristics of the flow as well as the complexity of the solu tion can vary signific antly depending on the order of magnitude of several key dimensi onless variables. The dimensionless governing equations yields key dimensionless groups that govern the flow and are found to be the local rotational (disk) Reynol ds number in terms of 1, the Euler number and the gap aspect ratio, S If the rotational speed of the rotor is in rad/s then these parameters are defined as 1 Rr S (514) 22 mR P Eu r (515) 2 1Rem (516) PAGE 162 162 where P in the Euler number corresponds to th e maximum pressure differential on the rotors outer boundary, i.e. the intake and exha ust conditions. It should also be noted that in rotating disk problems the rotational Reynolds number is utilized in stead of the radial Reynolds number which is defined as 1Re R mrv For the same flow conditions, the use of the latter is typically three orders of magnitude larger. Daily and Nece (1960) have identified four different modes of flow for given geometrical and flow characte ristics. Of interest in th is study are the laminar and turbulent cases corresponding to a close ga p where boundary layers on the rotor and endplate are merged. In this case a continuous va riation of the velocity across the axial gap exists. The rotational Reynolds number must be small in the gap, 1Re1 for this type of flow to exist. Separate boundary layers exist when the axial gap exceeds the total thickness of the two boundary layers. The c ondition for laminar flow can therefore be estimated from Daily and Nece (1960) as 125Re10 S. The Euler number which is defined as the ratio of the maximum pressu re differential to the centrifugal pressure produced during rotation is assumed large, i.e.1Re1 Eu The gap aspect ratio must also be substantially larger than unity. If these four conditions can be satisfied simultaneously then a zerothorder solution approximates th e solution to the NavierStokes equations. This solution consists of a power series of Re, e.g. 112 012ReRe... uuuu expanded around the asymptotic solution of Re approaching zero. Bein et al. (1976) concluded that this is a reasonable assumption for20 Eu It must be determined whether the followi ng analysis is valid for the flow of twophase fluid in the axial gap. Due to the vapor ization of liquid in the expanders cavity, the thermodynamic properties vary significantly. Co upled with the signi ficant variation of PAGE 163 163 intake and exhaust parameters, geometry of the leakage gap and rotational speed of the expander, the aforementioned constraints may not be satisfied. In or der to determine the operational conditions under which the anal ysis is valid the following operational parameters considered are presented in Table 53. It can be shown that the flow is laminar for all parameters investigated at lower rotational speeds, i.e. <500 RPM. Depending on the geometric size of the expander, the expa nders actual rotational speed realistically doesnt exceed this value. Based on the anal ysis of these operational conditions, an order of magnitude analysis of the fl ow dimensionless parameters is presented in Table 53. It maybe concluded that the zerothorder solution is appropriate. The location of the phase in terface in rotating, eccentric complex geometries is very difficult to predict. If sufficient centrifugal forces are produced due to high rotational speeds it may be assumed that the ma jority of the leakageflow in the axial gap is vapor. This arises due to th e tendency of the dense liquid to flow in the vicinity of the statorcylinder wall due to significant centrifugal forces. Hence the incompressible form of the general equations with c onstant properties, evaluated at some mean value, is used. Neglecting body forces, terms of order 1/ S2 and equating terms with Re1, the zerothorder dimensionless 3D NavierStokes equation s in cylindrical coordinates are solved in order to determine the velocity and pressure field within the narrow gap. If a gap width 1 exists between the rotor and the end plates then the dimensionless governing equations can be reduced and written as follows 00 011 0 vw ru rrrz (517) 12 00 2Re u p Eu zr (518) PAGE 164 164 12 00 21 Re v p Eu zr (519) 00 p z (520) where the dimensionless variables are defi ned in the nomenclature. According to Equation (520), 00, PPr The boundary conditions can be written as follows, (,,0)0ourz 0(,,0)0 vrz (,,0)0owrz (521) (,,1)0ourz 0(,,1) vrzr (,,1)0owrz (522) (1,)()ocvPrP 0 0(,)(,)0 P urr r (523) where Pcv( ) is a linear piecewise function that cl osely approximates the actual pressure distribution around the rotors outer boundary and is presented in Figure 54. A linear approximation first presented by Be in et al. (1976) an d furthered by Badr (1985) for a typical pressure profile is compared to nume rically integrated Fourier constants in Equation (525). It can be s hown that 100 terms in the summation of the Fourier constants yield the actual pressure distribution. Depending on the geometric volume ratio of the expander, the differen ce between the linear approximation and can vary significantly. An expande r with a volume ratio of rv=3.916 is analyzed in Figure 54 PAGE 165 165 and a maximum difference of 40% is found to exist between. This gr eatly influences the accuracy of the computed radial velocity. The zerothorder solution of the following simplified set of equations and satisfying all necessary boundary conditions yields Bein et al. (1976) as such 12 0 0Re () 2 Eu P uzz r (524) 12 0 0Re 1 () 2 Eu P vzzrz r (525) Substituting Equations (524) and (525) into the continuity equation, Equation (517), and applying the boundary conditions in the axial direction yields 2 00 P (526) Solving Equation (526) by mean s of separation of variables, the general solution for the pressure distribution in the gap is 000 1(,)ln cos()sinnnnn nnnn nPrabr arbrncrdrn (527) The Fourier constants can be determined from the specification of the pressure distribution on the outer boundary of the rotor (see discussion of Fi gure 54). The radial velocity distribution can be found by differen tiating Equation (527) with respect to the radial direction and substituting that result into Equation (523). The total dimensional leakage mass flowrate in the radial di rection with respect to the rotor is 2 ,10121,leakcvRmurr (528) PAGE 166 166 The value of the mass flowrate is negativ e if the flow leaves the expander cell. This model doesnt take into account choki ng, which is likely, since the velocity distribution at the rotors outer boundary is of primary interest. Leakage around tips of vanes Depending upon on the method by which the high pressure refrigerant is introduced into the expanders cavity; see Figure 51, leakage due to insufficient undervane fluid pressure or inadequate force/absence of mechanical springs may lead to significant leakage losses several orders of magnitude larger than other leak age paths. Continuous and sufficient contact between the vanes and th e statorcylinder is ne cessary to subdue or minimize this type of leakage. The majority of leakage of this type may occur during the intake process where low rotational speeds cause inadequate centrifugal forces to keep the vanes in contact with the statorcylinder. The existence of both low rotational speeds and inadequate undervane pressure can be pr edicted by the frictiona l model developed. The frictional model is presented later in this chapter. It should be noted that the reaction force, Fn( ) (see Figure 55), is pred icted by the friction model and accounts for, among other things, the sliding veloci ty and acceleration of the prot ruding vanes as well as the undervane pressure. If the vane ha s lost contact with the stato rcylinder, the value of this normal force is negative, and the leakage flow area would be computed as 2()()leak A LXL (529) where X( ) is the instantaneous protru sion of the vane from the rotor slot at the angular rotation of the rotor where the loss of contact has occurred. When the vanes establish contact with the cylinder it is assumed that the leakage area is negligible and that this occurs until the start of the sealing arc. There may exist PAGE 167 167 leakage around the tips of the vanes during the spread of the sealing arc due to a clearance gap between the statorcylinder and roto r that may be due to an assembly clearance or due to machining limitations. Th is radial leakage is treated in the next section. Due to the short nature of this leakage path, tv, the leakage of the twophase fluid in this path is assumed to be th at of fluid in a convergentdi vergent nozzle, i.e. isentropic flow. It should be noted that if the incoming fluid is introduced into the roto rs slots than the internal leakage as sociated with weak undervane pre ssure can be neglected. For this design, internal leakage around th e tips of the vanes can be neglected. The highpressure incoming refrigerant is first used to provi de sufficient undervane pressure so that continuous contact between the vane a nd statorcylinder may be achieved. Leakage past the sides of the vanes In general, the axial width of this leakage path may be estimated by accounting for the thermal expansion of the vanes in addition to the gap that exists due to the thickness of gaskets, g and other assembly clearances. The operational length of the vane can be computed from the known materials coe fficient of linear thermal expansion, ,, vvovvo L LLT, and the temperature difference that the vane encounters relative to ambient conditions. The mean temperature of the vane is computed as the average temperature of two adjacent cells. It can be shown that even at the moderate temperature differences realized within an expanders cavi ty this effect accounts for a 0.3% change in the length of the vane and is therefore neglected. The axial width of the leakage path is assumed constant and equivale nt to the gasket thickness 3 g (530) PAGE 168 168 The height of this leakage channel is estim ated by subtracting the height of the gap realized due to leakage around th e vane tips, if any, upon loss of contact with the statorcylinder, 2( ). The total leakage flow area is then calculated as 23()2()leakAX (531) Due to the short nature of this leakage path, tv, the leakage of the twophase fluid in this path is assumed to be that of fluid in a c onvergentdivergent nozzle, i.e. isentropic flow. Leakage between the faces of the vanes a nd the side walls of the rotors slots The leakage from this path is typically ne glected due to the exis tence of two contact lines across the axial length of the rotor slots. These contact lines result from the reaction forces FL ) and FR( ) (see Figure 55). Negative reaction forces predicted by the friction model represent a loss of contact between the vane and the rotor sl ot. The control volume to which the mass and energy are added or subtracted depends on which vane face the loss of contact occurs. If the fl uid intake is throug h the rotor slot the leakage through this path may be significant and comparable to other paths. Viscous effects need to be considered since the leakage fl ow path is wide and long, Hv. The leakage flow area is computed as ()()leaksvAttL (532) The Leakage from the expander to the cavity be neath the vane may also be comparable if tstv is large. Leakage in radial gap between the rotor and stator cylinder As the pressure differential between the in take and exhaust ports increases and the number of vanes decreases, this leakage is t ypically the largest contributor to internal leakage. PAGE 169 169 This leakage flow path arises if the angl e between successive vanes is larger than the spread of the sealing arc (spread of minimal clearance) between the rotor and statorcylinder i.e. seal If this is the case, the expander ce ll is in simultaneous contact with the intake and exhaust ports. This overlap causes leakage flow from the inlet to the exhaust ports against the direction of rotation. The severity of this leakage path is a function of the number of vanes and the mean radial gap height 4 that exists between the rotor and statorcylinder due to assembly operations or machining limitations. This leakage flow path would occur for the leading vanes angular displacement of 0 s eal The flow in this leakage path is modeled as adiabatic, onedimensional Fannoflow. It should be noted that leakage through this path can only be neglected if sufficient centrifugal forces or undervane pre ssure exists to mainta in continuous contact of the vane with the statorc ylinder. Typically an insuffici ent undervane force exists due to the absence of highpressure fluid (or presen ce of lowpressure re sidual fluid) due to the theoretical completion of the exhaust pr ocess. The magnitude of the normal force Fn( ) determined by the frictional model aids in this prediction. The flow in this leakage path would necessarily be choked for la rge geometric volume ratios or uncontrolled expansion in the exhaust por t if no throttle valve is dow nstream of the expander. Friction Model Prediction of the power output and devel oped torque of the rotaryvane expander requires accurate modeling of frictional loss es incurred in the expander. The primary frictional losses in the rotaryvane expander result from: Rubbing of the vanes agai nst the stat orcylinder Rubbing of the vanes against the walls of their rotors slots PAGE 170 170 The resultant viscous drag acting on both side s of the rotor from the leakage flows through the axial gaps between the rotor and the endplates. A steadystate mathematical model that pred icts frictional losses within a rotaryvane expander must be coupled with geomet ric, thermodynamic and to leakage models in order to provide for a better estimate of th e mechanical efficiency and actual power produced by the expander. A general dynamic mo del that incorporates the main sources of friction within the rotaryvane expander is pr esented in this section. Effects of pressure forces, reaction forces, sliding friction, viscous drag, gravity and inertial forces must all be accounted to understand the relevance and ma gnitude of these effects. Figure 55 is a schematic of a free body diagram of a vane pr otruding out a rotor slot at a local angle In order to model frictional losses in a ro taryvane expander, vane forces resulting from pressure loading, vane inertia a nd body forces due to radial and Coriolis accelerations must be determined. Sliding fric tion must also be considered between the vanes and the rotor slots and statorcyli nder. These forces and frictional losses continuously change, in both magnitude and direction throughout the expander due to continuous changes in complex geometry. The dynamic model developed assumes that the vanes are rigid and that the coefficient of friction is constant. The c onditions for dynamic equilibrium are solved simultaneously to determine the unknown reaction forces based on a freebody diagram of a single vane. Upon determining the reac tion forces, the power required to overcome the resisting frictional forces can be computed. Below is a detailed description of the various forces as well as simplifying assumptions that have been made. A pressure force on the base of the vanes is assumed to act at midthickness of the vane as a result of incoming fluid pressure or a spring force utilized to maintain vanetip PAGE 171 171 and statorcylinder contact. This pressure fo rce at the vane base can be expressed as follows b inletvFPtL (533) where is a proportionality consta nt that can be evaluated from calculating throttling losses to or from the cavity beneath the vane. If the fluid is introduced directly into the rotor slots for the spread of the intake port, in, and assuming no throttling losses then =1. If the fluid is introduced into the expa nders cavity directly then throttled leakage flow will provide the pressure force on the vane base (e.g. =0.75). If correctly sized and assembled springs or a means for adequate pressurization of the slots are used then =1. The pressure forces exerted on the vanes from either side FPR and FPL can be expressed as PLcvFPXL and PRcvFPXL respectively. If leakage losses through the vane rotorslot gaps are neglected then these pressure forces are assumed to act midway between the ro tors outer boundary a nd statorcylinders wall. If a gap exists between the vanes and the rotor slots, the orientation of the pressureloaded vane, see exaggerated effect in Fi gure 55, provides two sealing surfaces. The portion of the vane that protrude s from the slot is denoted by X( ). The reaction forces FL( ) and FR( ) are assumed to act at the points of contact of the vane and the rotor slots on the left and right faces of the slot, respectively. These forces are actually distribute d along a finite distance along the side of the vane and not at a point depending on the vanetoslot clearance. Since the vanes are assumed to be rigid, the friction forces are assume d to act along the surfaces as rLF and rRF respectively. The subscript r denotes th e rotor material. The reaction forces Fn( ) and PAGE 172 172 Ft( ) result from the vanetip and statorcylinder contact where nstFF The vanes are assumed to be in continuous contact with the statorcylinder. Th e subscript s denotes the statorcylinder material. The assu mption that the friction force (e.g. rLF) is proportional to the normal contact force (e.g. FL) may not accurate since large local velocity gradients at the inte rface may severally alter the fric tional losses. This may also be the case at the vanetip and statorcylinder interface. It should be noted that Figure 55 is valid for a vane that has no vanetip curvature. If the vanetip is round or altered in any wa y there will exist symmetric radial forces on either side of the normal force equal to the pressure on that side of the vane multiplied by the projected area of that surface. The sliding and centrifugal acc elerations of the moving vane from the rotor slot result in a radial body force Fa( ) which can be expressed as 2 avmFmAcc()r (534) where rm( ) denotes the distance from the center of the rotor to the center of mass of the vane. The mean tangential body force Fc( ) that arises due to Cori olis acceleration of the vane can be expressed as cvF2mVel (535) where Vel( ) and Acc( ) represent the sliding velocity and acceleration of the vane respectively. The mass of the vane is assumed to act at the geometric center of the vane (i.e. Hv/2 and tv/2). From the following freebody diagram, Figur e 55, the three conditions of dynamic equilibrium can be written as follows PAGE 173 173 brLrRvanFFFmgcosFF0 (536) LvcRPLPRsnFmgsinFFFFF0 (537) vv vcRvPLPRv vv snvrLrRX HH mgsinFFHXFFH 222 tt FHFF0 22 (538) where Equations (536) and (537) represent th e net summation of forces in the radial and tangential directions equal to zero respect ively. Equation (538) represents the net summation of moments about point O equal to zero wherein th e direction of rotation of the expander is assumed positive. It should be noted that the direc tion of some of the forces change depending on whether the vane s are protruding out dur ing the intake and expansion processes or forced back into th e vane slots during th e exhaust process. The three equations can be simplified, r earranged and written in matrix form as aXb (539) where matrix a represents the coefficients of the unknown reaction forces of matrix X= L R nF F F and matrix b contains known parameters such as pressure and body forces. Once this matrix is solved at each angular displacement of the leading vane the reaction forces can be determined. The reacti on forces in matrix X reveal the movement of the vane in the rotors slot and can predict the loss of contact with the statorcylinder or faces of the rotor slots. It should be noted that the coefficients in matrix a should be modified according to the vanes inward or outward movement relative to the slot. The PAGE 174 174 mechanical efficiency and power losses of the expander due to friction can then be predicted. The frictional tor que per angular displacement due to vanetip (first term) and net vaneslot friction (second term) can be computed from r sfsnRLRTF()rX()F()F()Vel() (540) The total frictional loss, Tsf,, in the expander is com puted by summing Equation (540) through a complete revolution of the ro tor. The contribution of each vane is accounted for and its contributi on to the total tor que is then averaged to yield Tsf,m. No rubbing frictional forces exist between th e sides of the vanes and the end plates due to the axial gaps between the rotor a nd the endplates. The leakage through those gaps, as determined previously, will lead to viscous drag. In order to model the viscous drag due to the axial leakage between the rotor and endplates the viscosity of the twophase flui d must be predicted accurately. The pressure distribution in the axial gap P(r, ) was derived previously. The pressure is assumed to be invariant in the axial direction. The state of the twophase liquid can be determined by assuming isenthalpic expansion in the radial and azimuthal directions. The flow in the axial gap is driven by both shear caused by the rotation of the disk and a pressure differential between the intake and exhaust ports. This results in a combined CouettePouisselle (generalized Couette) flow, see Figure 56, in which the radial velocity can be expressed as 2 1 11 ()()mdPr uzzzz dr (541) The total torque produced by viscous drag on both sides of the ro tor is expressed by PAGE 175 175 10 ,22RRrr vdm r rzdu Trrdr dz (542) which can be integrated numerically. The total power loss is then calculated by losssf,mvdPTT (543) where is the angular speed of the expander in RPM. Uncertainties regarding the gap size ar e a significant obstacle to quantifying the magnitude of leakage losses through certain leakage paths. These uncertainties are presented later. The base case simulations de tailed below are valid for an eight vane circular expander of general orientation (i.e. =161.5 and ()SRSr ) with a geometric volume ratio of rv=3.26 corresponding to in=35o and ex=189o whose physical dimensions mimic a modified GAST NL32NCC1 airmotor. Th e rotational speed of the expander is =300 RPM. The inlet conditions to the expander correspond to a saturated liquid at a condensing temperature of T=45oC. As previously mentioned, the estimated fr ictional forces within the expander are used to predict the movement of the vanes w ithin their rotor slots. The profile of the vanetip is of significant importance in de termining the forces acting on the vanetip. Figure 57 shows the instantaneous variation of reaction forces on a single vane with no vanetip curvature during one revolution of the rotor. It is assumed that a circular pressurizing grove ensures that =1 through out one revolution. It can be seen that the normal force tends to the same variation as th e pressure inside the expanders cavity due to the significant contribution of the undervane pressure and absence of resisting forces in the opposite direction. It should be noted that no loss of contact is predicted for any of the reaction forces. It can be shown that for vanes with no vanetip curvature an PAGE 176 176 insignificant undervane pressure ( =0.1) is necessary to maintain contact with the statorcylinder. Figure 58 is similar in nature to Figure 57 but for a vane that has curvature at the vanetip (i.e. addition of symmetr ic radial forces about normal force). It can be seen that the normal reaction force is negative, denoting a loss of contact, during in+ < < corresponding to a majority of the expansion process. The increased pressure gradient across the vane in this case may lead to excessive leakage losses. This information is passed to the appropriate internal leakage c ode. The use of materials such as graphite, erode and match the profile of the statorcy linder depending on the intensity of the undervane pressure. The density of the material should be large enough to provide sufficient centrifugal forces if and when inad equate undervane pr essures exist. Simulations were run to find the minimum value of in order to obtain a positive reaction force at the vanetip statorcylinde r interface denoting contact with the statorcylinder. Values of =0.75, 0.85 and 0.95 were simulate d. It was found that due to the curvature of the vanetip, only a value of >0.95 would suffice. Figures 59 through 512 show the variation of leakage to and from the expander cavity by different leakage paths through one revolution of the rotor. Figure 59 shows the variation of nonax isymmetric leakage from the expander cavity as a function of angular displacement for different intake angles. It is ensured that the governing dimensionless vari ables satisfy the c onstraints and assumptions that govern the flow. The use of choked flow relations for this leakage path does not grasp the underlying physics; magnitude and direction, as sociated with the flow between a rotating and stationary disk with nonaxisymmetric boundary conditions. It can be shown that if PAGE 177 177 choked flow conditions are assumed at the rotor boundary then the leakage from, model cannot predict otherwise, the expander cavity is over predic ted throughout the majority of the intake and exhaust processes. The curre nt analysis overpredicts the cell leakage when compared to the choked flow model duri ng the expansion process solely due to the accuracy of the pressure pr ofile used to approximate the nonaxisymmetric boundary condition. Figure 510 illustra tes the variation of the nonaxisymmetric leakage as a function of angular displacement for both the id eal and throttling cases. As the inlet angle decreases the potential for leakage increases significantly during the charging and expansion processes. For all leakage paths considered, the velo city of the leakage flow is calculated initially using the general Couette flow velocity profile determined above. If the flow is twophase, the speed of sound is calculated to provide a reference. If the computed velocity using the general Couette flow model exceeds the speed of sound, then the model switches over to a choked flow regime corresponding to a maximum leakage flowrate. These general trends are apparent from Figure 511. Figure 511 illustrates the total variation of flow to/from the expander cavity by means of leakage past the sides of the vane s. Contact between the vanetip and statorcylinder is assumed. A constant gap size is assumed. In actual operation, upon loss of contact, the vanes do not necessa rily retract all the way back into the rotor slot leaving the leakage channel height X( ) as assumed in the above derivation. The leakage mass flowrate during the constant pressure inta ke and exhaust processes can be seen to increase and decrease, respectively with the oscillating variation of vane protrusion X( ). This effect is more evident in expander s with a larger geometric volume ratio. PAGE 178 178 The leakage mass flowrate through the mini mal gap that exists between the rotor and the statorcylinder is significan t but constant for the duration 0< < seal, where seal is 40o. The contribution of this l eakage path to the total leak age flowrate increases with the decrease of the number of vanes. The star t of the intake port may be delayed, if necessary, to minimize leakage from this path. The magnitude and direction of the leakage between the sides of the vanes a nd the rotor slots depends on the method by which the fluid is introduced into the expa nders cavity. Figure 512 shows the variation of leakage into the expander cavity as a function of angular displacement. This leakage path only exists for the duration of the in take port. There may be leakage from the expander cavity via this leakage path during th e remainder of one revolution. If the flow is introduced through the rotor slots, the ve locity of this leakage path, assuming no throttling, would be that of an incompre ssible liquid in shear driven Couette flow. Here the plate moves with a velocity co rresponding to the instantaneous sliding velocity of the vane. The leakage mass flowra te can be seen to increase proportional to the outward sliding velocity of the protruding vane. Of primary significance for an adequately designed expansion devi ce is the ratio of total mass flowrate accounting for leakage and the corresponding ideal case, i.e. a leakage ratio actual idealm m The mass flowrate through the expander accounting for leakage is 5 0160lki actualvcv im mNm (544) PAGE 179 179 where the first term in the bracket repr esents the ideal mass flowrate and index i represents the leakage path. For the base case simulations the leakage ratio is =10.9. This is significantly large and due to the low rotational speed of 300 RPM. Figure 513 shows the variation of the ideal and actual mass flowrates as a function of rotational speed. It can be seen that the leakage mass flowrate decreases significantly as the rotational speed of the e xpander is increased. The ideal mass flowrate increases in a steady manner. The operational rotational speed of th e expander is a design choice that may be optimized by the proper se lection of volumetric displacement for the inlet flow conditions. The leakage ratio is =30.6 and 4 at rotati onal speeds of 100 and 1000, respectively. The actual mass flowrate cu rve increases linearly because all of the internal leakage paths, with the exception of axial flow between the rotor and endplates, is assumed to be independent of speed. Figure 514 illustrates the variation of th e ideal and actual mass flowrates as a function of the number of vanes for an expander operational speed of 500 RPM. The ideal mass flowrate decreases since the volum e of the cavity and the amount of mass in the expander cavity at the cutoff angle decr eases significantly. The amount of leakage is seen to increase due to a larger contribu tion from the leakage ma ss flowrate through the radial gap, minimum clearance, between the ro tor and statorcylinder. Caution must be exercised when increasing the number of vane s due to possible increases in friction and decrease of mechanical strength of the rotor. A thermodynamic and fluid dynamic model of the primary loss mechanisms in a circular rotaryvane expander has been de veloped as a function of design and fluid parameters. The following conclusions can be made: PAGE 180 180 The curvature of the vanetip can severall y impact the amount of leakage past the vanetips due to loss of contact with the statorcylinder. Even if no throttling is assumed in the intake port, there is a loss of contact w ith the statorcylinder through out the duration of the expansion process. Vanes should be made out of highdensity ma terials that can erode and mold to the statorcylinder geometric curvature. This would eliminate the need for adequate undervane forces through intake ports or cumbersome, unreliable springs. Leakage losses from a majority of leakag e paths cannot be nece ssarily neglected in twophase rotaryvane expanders. Unlike si nglephase rotaryvane turbomachinery, significant variation in dens ity and speed of sound with the vaporization of liquid significantly alters the leakage flowrates. The leakage losses from the nonaxisymmetr ic flow in the axial gap between the rotor and endplates is significant. The m odel developed is relatively ideal in its assumptions and doesnt take into acc ount separated boundary layers, choking or turbulent fluid flow. A computational m odel must solve the compressible NavierStokes equations in order to do so. Increase in rotational speed decreases internal leakage losses significantly. Further work must be made to determine the magnitude of detrimental effects such as friction and viscous drag. A decrease in the number of vanes increases the contribution of leakage through the minimal radial gap between the rotor and stator cylinder. Sizing of the rotaryvane expander for twophase applications is critical with regard to determining the optimum operational speed to reduce the loss mechanisms presented in this study. Uncertainties regarding the gap size ar e a significant obstacle to quantifying the magnitude of leakage losses through a ll the leakage path s during operation. TwoPhase Throttling Losses in the Inlet and Exhaust Ports The state of refrigerant that enters the expansion device is of great importance. Unlike the conventional thrott ling valve, the state of the refrigerant may vary significantly from condenser exit conditions to the expander cavity. This may be due to significant throttling losses within the inlet port and internal contra ctions, enlargements and bends within the expansion device. This ma y also be partly due to the fact that the distance downstream over which the influence of the feature is felt is greatly increased in PAGE 181 181 twophase flow. A model for the prediction of the pressure losses of twophase flow due to these flow restrictions is presented. An algorithm is presented and developed by which the actual state and amount of refrigerant entering the expans ion device can be computed. Figure 515 illustrates the difference between the conventional and modified methods of intake. The refrigerant leaving the condenser may be either saturated or subcooled liquid. Depending on the degree of subcooling, pressu re drops resulting from throttling in the expanders intake port and friction due to flow restrictions may cause the refrigerant to drop into the twophase region. These pressure losses should be minimized in order to maximize the pressure differential utilized to produce work in the expander. In the case of underexpansion, where the geometric volume ratio is not sufficient when compared to the process volume ratio, pressu re losses realized in the intake and exhaust ports are a necessary loss mechanism after which no further throttling may be needed. The analysis of throttling in the ports can be divided into two distinct analyses. The difference in analysis depends solely on the method the refrigerant enters the expander cavity. The equations for the static pressure drops, frictional pressure losses and contraction coefficients for va rious geometries are presented below. Calculating throttling losses and the actual mass flowrate is presente d later. This will aid in the evaluation of how well modeling the intake and exha ust processes as isobaric is. During the intake process the refrigerant goes through numerous pressure drops as a result of contractions a nd bends. The following assumptions are made to simplify the analysis for all geometries unless otherw ise specified. The void fraction of the homogenous twophase mixture is assumed constant over the feature (i.e. no phase PAGE 182 182 change). Separation of the two phases occu rs and the use of ge neral singlephase frictional loss methods are no longer valid. The following correlations, from Collier (1972) are presented to cal culate the static pressure drop, Equation (545), and the fric tional pressure loss across a contraction, Equation (546). A simplified momentum balance for the combined flow yields 2 2 fg 2f 12 2 cfv Gv 11 pp111x 2Cv (545) 2 2 fg 2f f cfv Gv1 p11x 2Cv (546) where Equations (545) and (546) differ by a factor 21 1 which represents the conversion of pressure energy to theoreti cal kinetic energy associated with the acceleration of the fluid through the contraction. The symbol is the ratio of the upstream A1 to downstream area A2. G2 is the mass velocity of the refrigerant and is defined as the velocity at the downstream location to the specific volume at that same location. Cc is the coefficient of contraction and is defined as the ratio of minimum area Ac to downstream area A2. This minimum area Ac, see Figure 516, corresponds to the narrowest cross section where the smalle st local pressure value is found. In order to calculate the coefficient of c ontraction, the twophase empirical relation presented by Ruffell (1978) according to Schmidt and Friedel (1997) is used. The equation for the contraction coefficient can be written as PAGE 183 183 c1 1 C1 1 2.08010.5371 (547) Equation (547) has been compared against the contraction coefficients for turbulent singlephase flow presented by Perry (1963) in Table 54. It should be noted that both models have been determined experimentally It has been found that modeled pressure drop across sudden contractions is satisfactory and that the constant void fraction assumption is not necessarily accurate (Collier (1972)). Upon exit from either the 90o bends or the expander cavity, sudden enlargement may exist in which further pressure losses are realized. For a twophase mixture, the change in static pressure and total frictional pressure drop across the enlargement can be determined from a simplified momentum ba lance for the combined flow written as fg 2 211f fv ppG1v1x v (548) 2 2 fg 1 ff fv G p1v1x 2v (549) where G1 is the mass flux upstream of the sudden enlargement. The homogenous and constant void fraction pressure drop models presented above may yield satisfactory predictions since low mass velociti es and pressures are expected. In the case of twophase flow through a sharp edged orifice, the discharge coefficient is equivalent to the contracti on coefficient if sma ll amounts of frictional dissipation and velocity profile effects are neglected (Collie r (1972)). The pressure drop equation that results from a simplified momentum balance, assuming a homogenous PAGE 184 184 mixture and constant void fraction through the orifice, must be modified using a twophase multiplier The pressure drop in a uniform flow area, 90o bend can be calculated from the following equation presented by Collier (1972) gg 12 fffpp pp 1C ppp (550) where Pf and Pg are the pressure drops for the li quid and vapor phases and are defined as 2 2 f f 22 Dm1xv p 2CA (551) 22 g g 22 Dmxv p 2CA (552) where the discharge coefficient CD is approximated as the coe fficient of contraction Cc from Equation (547). This assumption neglects the small amount of frictional dissipation and velocity effects that may be incurred dur ing the flow. The constant C is evaluated from the following general expression 0.50.50.5 2fggf gfgvvv CC vvv (553) where =1 and the constant C2 is 2135D C L for 90o bends or 2120D C L for 90o bends with an upstream disturbance. Conventional Inlet to Expander Cavity As mentioned previously, this inlet port is typically machined into the statorcylinder. The inlet port spread is a design parameter with significant impact on the PAGE 185 185 volumetric efficiency and thermodynamic perf ormance of rotaryvane technology. This may be of greater concern in twophase e xpanders since pressure drops in twophase flows are inherently la rger and necessitate the formati on of vapor. Depending on several factors including the spread of the intake port, the angle between successive vanes and the angular location of the lead ing vane relative to the intake port, the intake manifold will be in continuous contact with one or more of the expander cells. It should be noted that due to this continuous contact pulsation effects are ne gligible. It is hence of importance to calculate the actual mass flowra te of incoming refrigerant into each cell and the impact it may have on the performance of the expansion device. An optimal design of the intake port would minimize fl ow restrictions that would alter flow characteristics by maximizing the available fl ow area at each angle of rotation. This would ensure that an equal veloc ity is obtained at every opening. To capture the effect of irreversible losses that are inherent in the intake port due to flow restrictions, the concept of the discharge coefficient mu st be introduced. In general the discharge coefficient is defined as the ratio of the actual to ideal mass flowrates. The discharge coefficient is a st rong function of the area ratio and the Reynolds number of the flow. The flow through the conventional inta ke port can be modeled as that of a twophase flow through a sharpedged orifice. In the case of twophase flow through a sharp edged orifice, the discharge coefficient is equivalent to the contraction coefficient, Equation 547, if small amounts of frictional dissipation and velocity profile effects are neglected (Collier, 1972). A schematic of the th ree phases of vane orientation that occur during the intake process are shown in Figure 517. PAGE 186 186 It can be shown that the time rate of cha nge of volumes on either side of the leading vane in phase I, for example, differ signifi cantly. This alters the amount of mass that enters either control volume. The throat that is formed in phases I and III constitutes a major flow restriction. The definition of the discharge coefficient may be altered to incorporate the effect of the fo rmation of the throat as well as the discrepancy in the timerate of change in expander cavity volume. An area averaged, change in volume weighted component is incorporated into the defin ition of the discharge coefficient as such 1 2() ()()in dc refA V CC VA (554) where Aref is a reference area that denotes a frictio nless orifice area that produces an ideal massflowrate. Figure 518 shows the variation pressure within the expander cavity as a function of the angular displacement of th e leading vane for the ideal and actual (throttling only) cases. It can be seen from Figure 518 that a signi ficant drop in pressure is realized in the intake and expansion phases. This dramati cally reduces the expanders performance by reducing the volumetric efficiency and generated torque and pow er. For all else equal, the volumetric efficiency is defined as the ratio of the actual density at the cutoff volume to ideal density (i.e. inlet density). The variati on in the volumetric efficiency, final pressure in the expander cavity at the maximum volume, are tabulated in Table 55 for various intake angles. Standalone experiments are n eeded in order to accurate ly determine the variation of the discharge coefficient. One discrepanc y that may exist is that at smaller local rotation angles, the discharge coefficient may in fact approach unity and decrease in a PAGE 187 187 near linear fashion. This trend is repres ented as the dotted line in Figure 518. This situation arises from the fact that both the time and volume required to be filled initially is very small and that the extremely small throat area provides for a entrainment free jet of working fluid to fill the expa nder cavity in question. At larg er angles of rotation, there may exist entrained fluid that di srupts and alters the flow. It should be noted that the throttling losse s in the exhaust port are typically found to be negligible due to the smaller velocities as sociated with the exhaus t fluid and the larger spread area of the exhaust port. Modified Inlet to Expander Cavity The flow of the twophase re frigerant in the intake is assumed to be homogenous and gravitational effects on the pr essure drops in vertical porti ons of the intake have been neglected. The pressure drops associated with the work nece ssary to protrude the vanes has also been neglected. This may be the cas e since the centrifugal forces exerted on the vane due to rotation of the expander are typically an order of magnitude larger. In order to model the mass flow of refrigerant into the expander, the velocities of the fluid in the contractions, bends and enla rgements, the unk nowns, must be calculated. Figure 519 shows a schematic of the intake of a modified rotaryvane intake. The solution procedure entails an iterative procedur e in which the pressure at location 2 must be initially estimated as the average of the known pressures at locations 1 and 5. Using Equation (545), the velocity at Lo cation 2 may be calculated. Location 3 is denoted by an because in fact it represents 4 bends of equal flow area. For the sake of brevity they are illustrated as one. The veloc ities within these bends are assumed to be equal. Using Equation (550) the pressure at each of the bends can be calculated. Since the flow is compressible the quality at each one of these locations can be computed by PAGE 188 188 assuming an isenthalpic process. Using Equati on (548) the pressure at Location 4 can be computed since the mass velocity at 3* is known. The final parameter to be determined is the velocity at Location 4, wh ich can be computed using 2 441 2exit p u (555) This iterative procedure is repeated un til the initial guess of the pressure at Location 2 converges to within of the following 1523'argcontenleexit p ppppp (556) It should be noted that the pressure at th e exit can be determined using simulation models or from experiments. The mass flowrate can be computed as nnmuA where n=2,3*,4 Thermodynamic Model of the Actual Expansion Process In this section the effects of internal l eakage losses, friction and throttling are taken into account deriving the appropriate cons ervation of mass and energy equations. The solution procedure is detailed. The ideal predicted pressure, temperatur e and mass variations in the expanders control volume are used as in itial estimates when calculating any nonideal effects. The velocity and hence mass flowra te of the leakage flows via different leakage paths have already been presented. Charging Process The first law of thermodynamics, taking into account heat transfer generated by friction, frictional power losses and effects of internal leak age, can be written for the process as follows PAGE 189 189 intint,,,,cv f bfleakinleakinleakoutleakoutdE QWWmhmhmh dt (557) Assuming the changes in kinetic ener gy and potential energy are neglected dEcv=dUcv. The pressure within the control vol ume is also assumed to be uniform. Multiplying by dt Equation (557) becomes 121intint,,,,() f fleakinleakinleakoutleakoutUqpVVwmhmhmh (558) Solving for the internal energy of the refrig erant at the new time step, State 2, we find 11121intint,,,, 2 2,,() f fleakinleakinleakoutleakout leakinleakoutmuqpVVwmhmhmh u mmm (559) The density of the refrigerant at the ne w time step, State 2, is calculated as 2,, 2 2leakinleakoutmmm V (560) The use of REFPROP 7.0 allows the determination of the thermodynamic properties at the new state point, State 2, name ly the temperature, pressure and quality. The process is repeated until the end of the charging process. Expansion Process Unlike the ideal expansion process the mass in the control volume, mcv, varies depending on the magnitude of the internal leakage losses after the cutoff angle intcut. The density at State 2 can be determined from 1,, 2 2 leakinleakoutmmm V (561) An energy balance of the control volume, i. e. leakage, during the expansion process yields the internal en ergy at State 2 as PAGE 190 190 11121,,,, 2 2,,() f fleakinleakinleakoutleakout leakinleakoutmuqpVVwmhmh u mmm (562) The thermodynamic properties at the new tim e step, namely temperature, pressure, and quality, can be calculated from Equations (561) and (562) by the use of REFPROP 7.0. This process is repeat ed until the end of the expansi on process at a predetermined design angle of ex. Exhaust process The exhaust process occurs at an exhaust angle ex until out end, where out is the spread of the exhaust port and is the angle between consecutive vanes. The first law of thermodynamics can be writ ten for the process as follows ,,,, cv f bfexexleakinleakinleakoutleakoutdE QWWmhmhmh dt (563) Assuming the changes in kinetic ener gy and potential energy are neglected, dEcv=dUcv. The pressure within the control volum e is also assumed to be uniform. The refrigerant flow from the control volume is also assumed to be quasisteady and homogenous. Multiplying Equation (563) by dt and solving for the internal energy of the refrigerant at the new time step, State 2, we find 1121,,,, 2 2,,() f exfexexleakinleakinleakoutleakout leakinleakoutmuqpVVwmhmhmh u mmm (564) The density of the refrigerant at the ne w time step, State 2, is calculated as 2,, 2 2 leakinleakoutmmm V (565) The use of REFPROP 7.0 allows the determination of the thermodynamic properties at the new state point, State 2, na mely the temperature, pressure and quality. PAGE 191 191Expander Performance Evaluation Upon development of the geometric, therm odynamic, internal leakage, frictional, throttling and any other loss mechanism, the overall performan ce of a rotaryvane expander can be predicted. The following pa rameters describe the performance of the expander with respect to different criteria. Of primary importance to the performance of any positive displacement expansion device is the geometric (builtin) volume ratio. This parameter is defined as the ratio of volumes at the exhaust and cutoff angles respec tively. The reader is referred to an earlier chapter dealing with this parameter in further detail. Along with the geometric volume ratio the geometric code deve loped allows for design optimization with regards to the number of vanes, location of intake and exha ust ports, statorcylinder geometry and size, rotor size and eccentricity and aspect ratio to name a few. The pressure, quality and mass variati ons of the working fluid within the expanders cells are predicte d by utilizing the thermodynamic model. Models for the intake and exhaust processes are used in conjunction with the thermodynamic model to determine throttling losses (termed breathing in the open literature) within the ports. These throttling losses are a primary function of port design (geometry) and spread (size). The use of these models also allows us to calculate the volumetric efficiency, resultant power ratio and efficiency of the multivan e expander due to throttling losses in the intake port. The volumetric e fficiency may be defined as int vcvinv v (566) where vint is the specific volume of the working fluid within the expanders cell assuming no throttling losses (i.e upstream conditions) and cvinv is the ensuing specific PAGE 192 192 volume of the refrigerant if there exists thro ttling within the intake port. Both quantities are calculated at the cutoff angle. As the vol umetric efficiency decreases, the effects of throttling significantly alter th e torque generated by the pre ssure forces exerted on the vanes by the working fluid and hence lead to a decrease in the us eful power output and efficiency of the expander. The power ratio, Pr, may be defined as the ratio of the power produced when throttling is accounted for to the ideal pow er produced by the expander with no throttling losses. Since the mass of refrigerant contained w ithin the cell volume of the expander at the cutoff volume may be signi ficantly less when throttling e ffects are considered, it may be advantageous to define a thermodynami c efficiency based on the ratio 