1. Combustion Team Supersonic Combustion 6/2/20151NASA 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 Purpose Final Design Intake Manifold Testing New Ignition System – Three way ignition 6/2/2015NASA Grant URC NCC NNX08BA44A2

3. Purpose To achieve and sustain Mach 1.0 to 2.0 speed, induce mixing and sustain combustion for a duration 6/2/2015NASA Grant URC NCC NNX08BA44A3

4. Initial Design 6/2/2015NASA Grant URC NCC NNX08BA44A4

5. Combustion Chamber Modifications Combustion Chamber Shortened Reduced Aspect Ratio 6/2/2015NASA Grant URC NCC NNX08BA44A5

6. Final Design 6/2/2015NASA Grant URC NCC NNX08BA44A6

7. Intake Manifold 6/2/2015NASA Grant URC NCC NNX08BA44A7

8. Purpose of Intake Manifold Will assist in premixing concept Determine if injection of hydrogen will effect nozzle performance If no effect is determine we will introduce – Hydrogen – Silane 6/2/2015NASA Grant URC NCC NNX08BA44A8

9. Intake Manifold Progress 6/2/2015NASA Grant URC NCC NNX08BA44A9 Side View FrontView

10. Intake and Nozzle 6/2/2015NASA Grant URC NCC NNX08BA44A10

11. Dr. Wu Pressure Adaptor 6/2/2015NASA Grant URC NCC NNX08BA44A11

12. Pressure Testing Used pressure adaptor to determine if hydrogen gas will effect nozzle performance. Comparing past nozzle value with intake manifold and hydrogen gas set up Hydrogen gas did not affect nozzle performance 6/2/2015NASA Grant URC NCC NNX08BA44A12

13. Pressure Reading at Nozzle Exit Pressure gage reading Anderson’s text: Mach 2.6 Area ratio: 2.89

14. New ignition System Three Tesla coils ( one for each spark plug) 13 V DC 1 Amp power source that is button operated All wire will be insulated and routed away from any flammable sources 6/2/2015NASA Grant URC NCC NNX08BA44A14

15. New Ignition Source: Tesla Coil Allows for continuous spark Tested strong spark across air flow Resonant transformer circuit 6/2/2015NASA Grant URC NCC NNX08BA44A15

16. Final Design 6/2/2015NASA Grant URC NCC NNX08BA44A16

17. Future Work Test hydrogen combustion at high pressure Acquire silane Finish combustion chamber Continue testingtesting 6/2/2015NASA Grant URC NCC NNX08BA44A17

18. Acknowledgements Many Thanks! Dr. Darrell Guillaume Dr. Chivey Wu Dr. Helen Boussalis Combustion Team UAV Team Special thanks to Solomon Yitagesu

19. Timeline 2009 - 2010 Hypersonic Combustion Team Timeline: February 2011 - March 2011 2011 Student NameFEB Mar Sara Esparza Finish fabrication of combustion chamber Built Telsa Coil Test Intake with Hydrogen Find machine Shop to Polish intake surface Fluent analysis of hydrogen and air inside intake mixture Determine the possibility of premixing hydrogen Cesar Olmedo Finish fabrication of combustion chamber Purchase Third Telsa Coil Fabrication of new Dr Wu Pressure Adapter Test Intake with Hydrogen Fabricate new intake test holder Fluent analysis of combustion chamber 10//2009NASA Grant URC NCC NNX08BA44A

20. 6/2/2015NASA 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”. 20

21. 6/2/2015NASA 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. 21