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Rocketdyne R-6636-L FINAL RE PORT FLUORINE-HYDROGEN

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Rocketdyne R-6636-L FINAL RE PORT FLUORINE-HYDROGEN (THRU) ° %/ / (PAGES) (CODE:) NASA CR-5497_ _-_ (NASA CR OR TMX OR AD NUMBER) (CATEGORY) Rocketdyne R-6636-l FINAL RE PORT FLUORINE-HYDROGEN PERFORMANCE EVALUATION .J PHASE I, PART I : ANALYSIS, DESIGN, AND DEMONSTRATION HIGH-PERFORMANCE INJECTORS FOR THE LIQUID F LUORINE- GASE OUS HYDROGEN PROPE L LANT C OMBINATION By GPO PRICE $ i{ H. A. Arbit CFSTI PRICE(S)•$ So Do Clapp Hard copy (HC) Microfiche (M F) ff 653 July 65 prepared for NATIONAL AERONAUTICS AND SPACE ADMINISTRATION Contract NASw- 1229 ROCKETDYNE RESEARCH DEPARTMENT North American Aviation, Inc. 6633 Canoga Avenue, Canoga Park, California NOTI CE This report was prepared as an account of Government sponsored Work. Neither the United States, nor the National Aeronautics and Space Administration (NASA), nor any person acting on be- half of NASA: A.) Makes any warranty or representation, expressed or implied, with respect to the accuracy, completeness, or usefulness of the information contained in this report, or that the use of any information, apparatus, method, or process disclosed in this report may not infringe privately owned rights; or B.) Assumes any liabilities with respect to the use of, ¢ or for damages resulting from the use of any infor- mation, apparatus, method or process disclosed in this report. As used above, "person acting on behalf of NASA" includes any employee or contractor of NASA, or employee of such contractor, to the extent that such employee or contractor of NASA or employee of such contractor prepares, disseminates, or provides access to, any information pursuant to his employment or contractor with NASA, or his employment with such contractor. Requests for copies of this report should be referred to National Aeronautics and Space Administration Office of Scientific and Technical Information Attention: AFSS-A Washington, D.C. 205_6 J ] NASA CR-5_978 R0CKETDYNER-6636-1 FINAL REPORT FLUORINE-HYDROGEN PER20RMANCE EVALUATION, PHASE I, PART I: ANALYSIS, DESIGN, AND DEMONSTRATION OF HIGII PERFORMANCE INJECTORS FOR THE LIQUID FLUORINE- GASEOUS HYDROG]_ COMBINATION By H. Ao Arbit S. D. Clapp prepared for NATIONAL AERONAUTICS AND SPACE ADMINISTRATION July 1966 Contract NASw-1229 Technical Management NASA Lewis Research Center Cleveland, Ohio Advanced Rocket Technology Branch Paul Herr Rocketdyne Research Department North American Aviation, Inc. 6635 Canoga Avenue, Canoga Park, California FLUORINE-HYDROGEN PERFORMANCE EVALUATION, PHASE I, PART I: ANALYSIS, DESIGN, AND DEMONSTRATION OF HIGH PERFORMANCE INJECTORS FOR TIlE LIQUID FLUORINE- GASEOUS HYDROGEN COMBINATION Technically Reviewed and Approved By: R. B.'_Lawhead oroV; Chief Propulsion Applications Propulsion Processes Research Division and Applications Research Division '_j ProgramJ. FriedmanManager Small Engines Division August 1966 ii _OCKETD¥_E • A DIVISION OF NORTH AMERICAN AVIATION, INC FORE_i0RD This report was prepared in compliance with Article IX of NASA Contract NASw-1229, under Rocketdyne G. 0. 8708. NASA Program direction was provided by Mr. F. Stephenson, NASA Headquarters, Washington, D.C., and Mr. P. Herr, NASA Lewis Research Center. Mr. J. Friedman, Small Engines Division, was Pro- gram Manager for the subject contract. For that portion of the overall project carried out by the Research Division and reported herein, S. D. Clapp served as Responsible Engineer, and H. A. Arbi% as Project Engineer. ACKNOWLEDGMENT Important contributions to the conduct of the pro- gram and %o the preparation of report material were made by the following personnel: Bo J. Heckert J. P. Bo%% R. L. Fallack D. E. Zwald iii ]l:_l-OiE::]lr_...l_YD"_i_l_lITl__ • A DIVISION OF" NORTH AMERICAN AVIATION. INC. CONTENTS Foreword ..... iii Summary ...... 1 Introduction ........ 5 Experimental Apparatus ..... 9 Injectors ...... 9 Thrust Chamber . 23 Propellant Manifolds ..... 27 Experimental Facilities and Procedures 29 Test Facility .... 29 Instrumentation . 31 Calibration Procedures .... 36 Firing Procedures . _2 Results _3 Performance .... 43 Heat Transfer . 55 Discussion of Results .... 69 Performance . 69 Heat Transfer ...... 8O Concluding Remarks ..... 99 References ..... 101 Appendix A Design of Chamber Wall Heat Flux Isolation Segments 105 Appendix B Injector Pressure Drops and Propellant Injection Velocities i17 Appendix C Measurement Analysis Program ...... 127 V II. O tE:: libra, lIE: "1" ]D "II1{" ]_II ]E_ • A DIVISION OF NORTH AMERICAN AVIATION, I N C-_. Appendix D 133 Calculation of Corrected c* Efficiency • • • Appendix E 153 Measurement Error Analysis ........... Appendix F 169 0scilla%ory Combustion in Low-L* Chambers ....... Appendix G 175 Cold Flow S%udies ............. Appendix H 179 Calculation of Heat Flux and Heat Transfer Coefficients vi l_tOCic ETI)¥N I_ $ A DIVISION OF' NORTH AMERICAN AVIATION, INC. I LLU STRATI 0NS I. Comparison of LF2/GH 2 Performance Models; Chamber Pressure = I00 psia, Expansion Ratio = 60 ..... 6 2. Effect of Fluorine Droplet Size and Combustion Chamber Length on Percent of LF 2 Vaporized .... 12 5. Effect of Drop Size Parameter (Equation 2) on c _ Efficiency of LF2/GH 2 and LOX/GH 2 in Triplet Injectors ....... 16 4. Face View of Doublet/Showerhead Injector Showing Orifice Pattern .......... 18 5. Method of Assembly of Injector, Fuel Manifold, and Oxidizer Dome Showing Typical Orifice Feed Arrangements Used for the Triplet and Doublet/Showerhead Injector Patterns • • • 20 6. Face View of Triplet Injector Showing Orifice Pattern . 22 7. Thrust Chamber Schematic Showing Segmented Design and Dimensions . • • 25 8. View of Assembled Thrust Chamber Showing Segmented Construction and Method of Joining • . 26 9. Thrust Chamber Schematic Showing Locations of Heat Transfer Isolation Segments in Chamber Wall ..... 28 i0. Schematic Flow Diagram of Test Stand Yoke, Propulsion Research Area, as Used in LF2/GH 2 Experimental Program 50 II. Schematic Flow Circuit of Experimental System Showing Types and Locations of Instrumentation Transducers 32 12. Variation of Liquid Fluorine Density with Temperature at Indicated Pressures • • • • 54 15. View of 50-inch L W Chamber Mounted on Thrust Stand • 58 vii • A DIVISION OF NORTH AMERICAN AVIATION, INC(_ i_OCK ET DYi"ql E 12. Theoretical LF2/GH 2 Shifting Equilibrium Characteristic 48 Velocity at Indicated Chamber Pressures . • • 15. Corrected c W Efficiency, Doublet/Showerhead Injector, at Indicated Nominal Chamber Pressures. LW=50 inches . 49 16. Corrected c _ Efficiency, Triplet Injector, at Indicated Nominal Chamber Pressures. L*=3 0 inches ..... 5O 17. Corrected c * Efficiencies of Triplet and Doublet/ Showerhead Injectors in 3.2-Inch and lO-Inch L * Chambers 53 at Nominal Chamber Pressure of 100 psia .... 18. Variation of Corrected c * Efficiency With Chamber Length at Nominal Chamber Pressure of I00 psia and Mixture 54 Ratio of 15 ............... 19. Typical Circumferential Variations of Heat Transfer 56 Coefficient, Doublet/Showerhead Injector . • • 20. Typical Circumferential Variation of Heat Transfer 57 Coefficient, Triplet Injector • • 21. Axial Variation of Heat Transfer Coefficient, Doublet/ Showerhead Injector at Indicated Nominal Chamber Pressures 59 and Mixture Ratio of 12 ...... 22. Axial Variation of Heat Transfer Coefficient, Triplet Injector at Indicated Nominal Chamber Pressures and 6o Mixture Ratio of 12 • • " 25. Axial Variation of Heat Flux, Doublet/Showerhead Injector at Indicated Nominal Chamber Pressures and 61 Mixture Ratio of 12 ..... 24. Axial Variation of Heat Flux, Triplet Injector at 62 Indicated Nominal Chamber Pressures and Mixture Ratio of 12 25. Heat Transfer Coefficient as Function of Mixture Ratio 62 at Axial Position 5 viii / i / /I _OC_ETDYNE • A DIVP_tON OF NORTH AMERICAN AVIATION, INC. 26. Heat Transfer Coefficient as Function of Mixture Ratio at Axial Position 6 ..... 55 27. Heat Transfer Coefficient as Function of Mixture Ratio at Axial Position 7 ..... 66 28. Heat Transfer Coefficients of Triplet and Doublet/ Showerhead Injectors in 3.4-inch and 10-inch L* Chambers 68 29. Theoretically Derived Variation of c* Efficiency with Percent of Liquid Fluorine Vaporized in LF2/GH 2 Combustion . 7O 30. Micro-flash Photographs, Cold Flows of Single-Element Injectors with Water and Helium . 73 51. Schlieren Photographs, Cold Flows of Single-Element Injectors with Water and Helium . 7_ 32. Theoretically Derived Distribution of Velocity Along Axis of Circular Gas Jet . 76 33. Theoretically Derived Velocity Distributions in Axisymmetric Free Circular Gas Jet 77 3_. Typical Geometry, Doublet/Showerhead Injector, Showing Intersection of LF 2 Fans with GIt 2 Jets at Varying Distances from Injector Face . 79 35. Estimated Heat Flux due to Radiation as Fraction of Total Measured Heat Flux . 85 36. Ratio of Convective Heat Transfer Coefficient (h_) to Measured Heat Transfer Coefficient (hg), after Correcting for Estimated Contributions of Radiation and Chemical Recombination . 88 37. Plots of Equation Ii, for Each of the Three Indicated Heat Transfer Coefficients. Triplet Injector, Axial Position _(in Combustion Chamber) ...... 9O ix ][_i. O 9[_ ]ii[..I,.,.i=, ,..it ]l]p ..311_,-i_ ]E_ • A DIVISION OF NORTH AMERICAN AVIATION, IN_'. 38. Plots of Equation ii, for Each of the Three Indicated Heat Transfer Coefficients. Triplet Injector, Axial 91 Position 6 (Immediately Upstream of Geometric Throat) 59. Comparison of Experimentally Observed Heat Transfer Coefficients in the Nozzle Region of the 30-1nch L* Chamber with Values Obtained from the Bartz and 9_ Mayer Calculations. P =50 psia, M.R.=I2 C $0. Comparison
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