Combustion TeamSupersonic Combustion

04/18/23 1NASA Grant URC NCC NNX08BA44A

Faculty Advisors:

Dr. GuillaumeDr. Wu Dr. BoussalisDr. LiuDr. Rad

Sara Esparza

Cesar Olmedo

Alonzo Perez

Student Researchers:

Outline

• Purpose

• Final Design

• Intake Manifold

• Testing

• New Ignition System– Three way ignition

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Purpose

To achieve and sustain Mach 1.0 to 2.0 speed, induce mixing and sustain combustion for a duration

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Initial Design

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Combustion Chamber Modifications

• Combustion Chamber Shortened

• Reduced Aspect Ratio

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Final Design

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Intake Manifold

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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

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Intake ManifoldProgress

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Side View FrontView

Intake and Nozzle

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Dr. Wu Pressure Adaptor

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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

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Pressure Reading at Nozzle Exit

• Pressure gage reading

• Anderson’s text: Mach 2.6

• Area ratio: 2.89

05.0134

73.6

psi

psi

inlet

exhaust

P

p

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

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New Ignition Source:Tesla Coil

• Allows for continuous spark

• Tested strong spark across air flow

• Resonant transformer circuit

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Final Design

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Future Work

• Test hydrogen combustion at high pressure

• Acquire silane

• Finish combustion chamber

• Continue testing

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Acknowledgements

Many Thanks!

• Dr. Darrell Guillaume

• Dr. Chivey Wu

• Dr. Helen Boussalis

• Combustion Team

• UAV Team• Special thanks to Solomon Yitagesu

Timeline2009 - 2010

Hypersonic Combustion Team Timeline: February 2011 - March 2011

2011

Student Name FEB FEB FEB Mar

Sara Esparza

Finish fabrication of combustion chamber Built Telsa Coil

Test Intake with Hydrogen

Find machine Shop toPolish 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//2009 NASA Grant URC NCC NNX08BA44A

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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”.

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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” 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.

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