1. Combustion Team Supersonic Combustion 6/12/20151NASA Grant URC NCC NNX08BA44A Faculty Advisors: Dr. Guillaume Dr. Wu Dr. Boussalis Dr. Liu Dr. Rad Sara Esparza Cesar Olmedo Alonzo Perez Student Researchers:

2. Outline Recent testing Shortened Combustion Chamber Determination of Mach Speed – Schlieren – Transparent (acrylic) Chamber – Cold Flow Preheater Large Compressor Refuel Hydrogen Tank

3. Recent Testing Video Pressures – 65 psi air – 200 psi hydrogen Parameters do not prove supersonic combustion Schlieren photography needed

4. Temperature Data

5. Shortened Combustion Chamber Combustion can be held at a higher mach number Ensures that the mach number stays above one Less frictional loss Shorter mixing time

6. Pressure Measurement Reading depends on diameter size Pressure reading decreases as the diameter increases

7. Determination of Mach Speed Calculations Schlieren Imaging – Cold flow – Analyze shock wave profiles

8. Schlieren Imaging Acrylic chamber –Allows visualization –H Studios Haziza polishing Schlieren Imaging –Cold flow –Analyze shock wave profiles

9. Possible Results Overexpanded Pressure at nozzle exit lower than ambient Underexpanded Exit pressure greater than back pressure

10. Preheater Amptek Flexible Electric Heating Tape Enhances likelihood of combustion Reduces density and apparent pressure within chamber

11. Large Compressor Drives pressure ratio Overcomes pressure loss due to heat addition Larger mass flow rate – Longer testing time Miniature wind tunnel

12. Large Compressor Size: 80 Gallons Test time: 30 seconds

13. Refuel Hydrogen Tank Fuel supply Industrial Hydrogen Tank Praxair Customer

14. Future Work Schlieren setup and imaging Purchase compressor More Testing NASA Report USC Fluids Conference

15. Thanks! Any Questions?

16. Timeline 2011 Hypersonic Combustion Team Timeline: March 2011 - June2011 2011 Student NameMarchAprilMayJune Sara Esparza Finish fabrication of combustion chamber Schlieren Photography Setup & Analysis Test Intake with Hydrogen Publish Papers Test Full Thrust System in Wind Tunnel Fluent analysis of hydrogen and air inside intake mixture Determine the possibility of premixing hydrogen Cesar Olmedo Finish fabrication of combustion chamber Finalize Spark System and Strength Schlieren Photography Setup Test Intake with Hydrogen Publish Papers Test Full Thrust System in Wind Tunnel Fluent analysis of combustion chamber 10//2009NASA Grant URC NCC NNX08BA44A

17. 6/12/2015NASA Grant URC NCC NNX08BA44A Textbook References Anderson, J. “Compressible Flow.” Anderson, J. “Hypersonic & High Temperature Gas Dynamics” Curran, E. T. & S. N. B. Murthy, “Scramjet Propulsion” AIAA Educational Series, Fogler, H.S. “Elements of Chemical Reaction Engineering” Prentice Hall International Studies. 3 rd ed. 1999. Heiser, W.H. & D. T. Pratt “Hypersonic Airbreathing Propulsion” AIAA Educational Series. Olfe, D. B. & V. Zakkay “Supersonic Flow, Chemical Processes, & Radiative Transfer” Perry, R. H. & D. W. Green “Perry’s Chemical Engineers’ Handbook” McGraw-Hill Turns, S.R. “An Introduction to Combustion” White, E.B. “Fluid Mechanics”. 17

18. 6/12/2015NASA Grant URC NCC NNX08BA44A Journal References Allen, W., P. I. King, M. R. Gruber, C. D. Carter, K. Y Hsu, “Fuel-Air Injection Effects on Combustion in Cavity-Based Flameholders in a Supersonic Flow”. 41 st AIAA Joint Propulsal. 2005-4105. Billig, F. S. “Combustion Processes in Supersonic Flow”. Journal of Propulsion, Vol. 4, No. 3, May-June 1988 Da Riva, Ignacio, Amable Linan, & Enrique Fraga “Some Results in Supersonic Combustion” 4 th Congress, Paris, France, 64-579, Aug 1964 Esparza, S. “Supersonic Combustion” CSULA Symposium, May 2008. Grishin, A. M. & E. E. Zelenskii, “Diffusional-Thermal Instability of the Normal Combustion of a Three-Component Gas Mixture,” Plenum Publishing Corporation. 1988. Ilbas, M., “The Effect of Thermal Radiation and Radiation Models on Hydrogen-Hydrocarbon Combustion Modeling” International Journal of Hydrogen Energy. Vol 30, Pgs. 1113-1126. 2005. Qin, J, W. Bao, W. Zhou, & D. Yu. “Performance Cycle Analysis of an Open Cooling Cycle for a Scramjet” IMechE, Vol. 223, Part G, 2009. Mathur, T., M. Gruber, K. Jackson, J. Donbar, W. Donaldson, T. Jackson, F. Billig. “Supersonic Combustion Experiements with a Cavity-Based Fuel Injection”. AFRL-PR-WP-TP-2006-271. Nov 2001 McGuire, J. R., R. R. Boyce, & N. R. Mudford. Journal of Propulsion & Power, Vol. 24, No. 6, Nov-Dec 2008 Mirmirani, M., C. Wu, A. Clark, S, Choi, & B. Fidam, “Airbreathing Hypersonic Flight Vehicle Modeling and Control, Review, Challenges, and a CFD-Based Example” Neely, A. J., I. Stotz, S. O’Byrne, R. R. Boyce, N. R. Mudford, “Flow Studies on a Hydrogen-Fueled Cavity Flame- Holder Scramjet. AIAA 2005-3358, 2005. Tetlow, M. R. & C. J. Doolan. “Comparison of Hydrogen and Hydrocarbon-Fueld Scramjet Engines for Orbital Insertion” Journal of Spacecraft and Rockets, Vol 44., No. 2., Mar-Apr 2007. 18