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Combustion Team Supersonic Combustion

Sara Esparza Cesar Olmedo Alonzo Perez. Combustion Team Supersonic Combustion. Faculty Advisors:. Student Researchers:. Dr. Guillaume Dr. Wu Dr. Boussalis Dr. Liu Dr. Rad. Purpose. To achieve and sustain Mach 1.0 to 2.0 speed, induce mixing and sustain combustion for a duration.

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Combustion Team Supersonic Combustion

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  1. NASA Grant URC NCC NNX08BA44A Sara Esparza Cesar Olmedo Alonzo Perez Combustion TeamSupersonic Combustion Faculty Advisors: Student Researchers: Dr. Guillaume Dr. Wu Dr. Boussalis Dr. Liu Dr. Rad

  2. NASA Grant URC NCC NNX08BA44A Purpose To achieve and sustain Mach 1.0 to 2.0 speed, induce mixing and sustain combustion for a duration

  3. NASA Grant URC NCC NNX08BA44A Final Design

  4. NASA Grant URC NCC NNX08BA44A Intake Manifold

  5. NASA Grant URC NCC NNX08BA44A 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. NASA Grant URC NCC NNX08BA44A Intake ManifoldProgress Side View FrontView

  7. NASA Grant URC NCC NNX08BA44A Converging Diverging Nozzle SectionView FrontView

  8. NASA Grant URC NCC NNX08BA44A Intake and Nozzle Side View

  9. NASA Grant URC NCC NNX08BA44A Intake and Nozzle Front View

  10. NASA Grant URC NCC NNX08BA44A Combustion Chamber

  11. NASA Grant URC NCC NNX08BA44A Combustion ChamberProgress

  12. NASA Grant URC NCC NNX08BA44A Dr. Wu Pressure Adaptor Front View

  13. NASA Grant URC NCC NNX08BA44A Pressure Testing • Will use Dr Wu pressure adaptor to determine if hydrogen gas will effect nozzle performance. • Comparing past nozzle value with intake manifold and hydrogen gas set up

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

  15. NASA Grant URC NCC NNX08BA44A New ignition System • Three telsa 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

  16. NASA Grant URC NCC NNX08BA44A New Ignition Source:Tesla Coil • Allows for continuous spark • Strong spark across air flow • Resonant transformer circuit

  17. NASA Grant URC NCC NNX08BA44A Tesla Coil • Resonant transformer circuit • High voltage • Low current • High frequency alternating current electricity • Loosely coupled coil winding

  18. NASA Grant URC NCC NNX08BA44A Final Design

  19. NASA Grant URC NCC NNX08BA44A Future Work • Test new Intake manifold with hydrogen • Determine premixing option • Incorporate telsa coil • Develop new ignition system • Acquire silane • Finish combustion chamber

  20. NASA Grant URC NCC NNX08BA44A Timeline2009 - 2010

  21. 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. 3rd 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”. 9/7/2014 NASA Grant URC NCC NNX08BA44A 21

  22. 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”. 41st 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” 4th 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. 9/7/2014 NASA Grant URC NCC NNX08BA44A 22

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