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Performance Evaluation of a Rocket Engine. Mehmet O Louisiana State University LSU Digital Commons LSU Historical Dissertations and Theses Graduate School 1973 Performance Evaluation of a Rocket Engine. Mehmet O. Ozelsel Louisiana State University and Agricultural & Mechanical College Follow this and additional works at: https://digitalcommons.lsu.edu/gradschool_disstheses Recommended Citation Ozelsel, Mehmet O., "Performance Evaluation of a Rocket Engine." (1973). LSU Historical Dissertations and Theses. 2416. https://digitalcommons.lsu.edu/gradschool_disstheses/2416 This Dissertation is brought to you for free and open access by the Graduate School at LSU Digital Commons. It has been accepted for inclusion in LSU Historical Dissertations and Theses by an authorized administrator of LSU Digital Commons. For more information, please contact [email protected]. INFORMATION TO USERS This material was produced from a microfilm copy of the original document. 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Further reproduction prohibited without permission. OZEESEL, Mehnnet 0 . , 1946- EEKPOBMMCE EWLUATICN CF A ROŒET ENSINE. The louisiana State University and agricultural and Mechanical College, Ph.D., 1973 Engineering, chemical f. University Microfilms, A XERQ\Company, Ann Arbor, Michigan i i‘ ' © 1973 Mehmet 0. Ozelsel ALL RIGHTS RESERVED I THIS DISSERTATION HAS BEEN MICROFILMED EXACTLY AS RECEIVED. Reproduced with permission of the copyright owner. Further reproduction prohibited without permission. PERFORMANCE EVALUATION OF A ROCKET ENGINE A Dissertation Submitted to the Graduate Faculty of the Louisiana State University and Agricultural and Mechanical College in partial fulfillment of the requirements for the degree of Doctor of Philosophy in The Department of Chemical Engineering by Mehmet Ô. Ozelsel B.S., Robert College, 1969 M.S., Louisiana State Univeristy, 1971 May 1973 Reproduced with permission of the copyright owner. Further reproduction prohibited without permission. ACKNOWLEDGEMENT The author would like to extend his gratitude to Dr. Richard C. Farmer, under whose guidance and assistance this research was performed. The author would also like to thank the members of his committee. Dr. Ralph Pike, Dr. Bert Wilkins and Dr. Frank Groves for their helpful comments and especially Professor Andrew J. McPhate for his assistance and help in the numeri­ cal analysis of the problem. Acknowledgement is also extended to the Department of Chemical Engineering, Louisiana State University, and to the National Aeronautics and Space Administration, who have financed this research. The author wishes to thank the Dr. Charles E. Coates Memorial Fund, donated by George H. Coates, for financial assistance in the preparation of this manuscript. Finally, a special thanks is extended to my wife, Michaels, for her long hours of "computer widowhood" and for her consistent encouragement throughout this project. Reproduced with permission of the copyright owner. Further reproduction prohibited without permission. TABLE OF CONTENTS ACKNOWLEDGEMENT ....................................... il TABLE OF CONTENTS ....................................... i ü LIST OF T ABLES ........................................... V LIST OF FIGURES ..................... vii ABSTRACT .............................................. viii CHAPTER 1 INTRODUCTION ............................... 1 2 PERFORMANCE EVALUATION OF A ROCKET ENGINE........................................ 10 3 THE DEVELOPMENT OF THE DOWNSTREAM BOUNDARY CONDITION ...................... 24 4 TECHNICAL DISCUSSION ...................... 31 5 EXAMPLE PROBLEM ............................. 54 CONCLUSIONS AND RECOMMENDATIONS FOR FUTURE WORK . 84 NOMENCLATURE .......................................... 87 LIST OF REFERENCES 90 APPENDIX: COMPUTER PROGRAM A MAIN PROGRAM .................................. 93 B FORMATION OF ERROR FUNCTION ................ 102 C MINIMIZATION TECHNIQUE ...................... Ill D CALCULATION OF MACH NUMBER AND THE DEVELOPMENT OF FLOW AND THERMODYNAMIC PROPERTIES ............... 120 E CALCULATION OF MIXTURE ENTHALPY, ENTROPY AND FREE ENERGY ............................ 128 ill Reproduced with permission of the copyright owner. Further reproduction prohibited without permission. Page F COMPUTER PROGRAM LISTING 132 VITA ............. 164 iv Reproduced with permission of the copyright owner. Further reproduction prohibited without permission. LIST OF TABLES Table Page 2-1 Physical Losses and Their Magnitudes ..... 16 2-2 Effect of Energy Release Loss to the Performance Evaluation ...................... 21 4-1 Equations Used in the Analysis ................ 46 5-1 J-2 Engine Test Data ........................... 55 5-2 Stochiometric Coefficients, a i j .............. 55 5-3 Combustion Cheunber, Throat, and Exit Cross-sectional Areas Sealed to 1 gnv^sec Mass Flow Rate ................... 56 5-4 Adiabatic Flame Temperature Results Compared to Prozan's Analysis ............. 58 5-5 Post Combustion Results of Independent Variables at Different Entropy Levels Compared to Adiabatic Flame Results....................................... 60 5-6 Equilibrium Independent Set Compared to a Free Energy Minimization Study, 0/F Ratio = 5.5 62 5-7 Effect of Entropy on Throat Conditions .... 67 5-8 Change in Magnitudes of Conservation Equations at Different Equilibrium States ........... 69 5-9 Temperature, Pressure and Mach Numbers in the Subsonic Zone (-1.56% Change in Entropy ............. « 70 5-10 Temperature, Pressure and Mach Number in the Supersonic Z o n e ............................ 78 5-11 Temperature, Pressure and Mach Number in the Supersonic Zone (16 Nodes) ................. 82 5-12 Comparison of Test Data for a J-2 Engine with Computed D a t a ............................... 85 Reproduced with permission of the copyright owner. Further reproduction prohibited without permission. Page Curve Fit Coefficients for Different Temperature Range .............................1 6 1 vi Reproduced with permission of the copyright owner. Further reproduction prohibited without permission. LIST OF FIGURES Figures Page 1-1 Rocket Engine .................................... 2 1-2 Flow Zones in Rocket E n g i n e ....................... 4 1-3 Flow Through a Choken De Laval Nozzle ............ 6 2-1 Calculation of Vacuum Specific Impulse .... 13 4-1 Control Volume ................................... 34 4-2 Finite Area C o m b u s t i o n .......................... 34 5-1 Temperature vs. Number of Nodes in the Subsonic Region .......................... 72 5-2 Pressure vs. Number of Nodes in the Subsonic Region .......................... 73 5-3 Mach vs. Number of Nodes in the Subsonic R e g i o n .........................................74 5-4 Specific Heat Ratio vs. Number of Nodes in the Subsonic Region ........................... 76 5-5 Temperature vs. Number of Nodes in the Supersonic Region ............................ 79 5-6 Pressure vs. Number of Nodes in the Supersonic Region ............................ 80 5-7 Mach Number vs. Number of Nodes in the Supersonic Region ............................ 81 A-1 Basic Logic Diagram .............................. 96 A-2 Marching Procedure .............................. 98 B-1 Relative Bounds on Variables .................. 106 B-2 CSTFN Logic Diagram ............................. 107 C-1 Isocontours of the Error Function and the Minimization R ou t i n e .................... 112 vii Reproduced with permission of the copyright owner. Further reproduction prohibited without permission. In this study, the conventional means for relating combustion chamber energy release to the corresponding com­ bustion chamber environmental conditions is questioned. Current equilibrium techniques predict specific impulse
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