Combustion Team Supersonic Combustion

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Combustion TeamSupersonic Combustion
Faculty Advisors
Student Researchers

• Sara Esparza
• Cesar Olmedo
• Alonzo Perez

Dr. Guillaume Dr. Wu Dr. Boussalis Dr. Liu Dr.
Rad
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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
Side View
FrontView
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Intake and Nozzle
Side View
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Dr. Wu Pressure Adaptor
Front View
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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
• Andersons text Mach 2.6
• Area ratio 2.89

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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 SourceTesla 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

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Timeline2009 - 2010
Hypersonic Combustion Team Timeline February 2011 - March 2011 Hypersonic Combustion Team Timeline February 2011 - March 2011 Hypersonic Combustion Team Timeline February 2011 - March 2011 Hypersonic Combustion Team Timeline February 2011 - March 2011 Hypersonic Combustion Team Timeline February 2011 - March 2011 Hypersonic Combustion Team Timeline February 2011 - March 2011
2011 2011 2011 2011 2011 2011
Student Name FEB FEB FEB FEB Mar
Sara Esparza Finish fabrication of combustion chamber Built Telsa Coil Built Telsa Coil Test Intake with Hydrogen Find machine Shop to Polish intake surface
Sara Esparza Fluent analysis of hydrogen and air inside intake mixture Determine the possibility of premixing hydrogen Determine the possibility of premixing hydrogen Test Intake with Hydrogen Find machine Shop to Polish intake surface
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
Cesar Olmedo Fluent analysis of combustion chamber Purchase Third Telsa Coil Fabrication of new Dr Wu Pressure Adapter Test Intake with Hydrogen Fabricate new intake test holder
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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 Perrys Chemical
  Engineers Handbook
• McGraw-Hill
• Turns, S.R. An Introduction to Combustion
• White, E.B. Fluid Mechanics.

4/8/2015
NASA Grant URC NCC NNX08BA44A
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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 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. OByrne, 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.

4/8/2015
NASA Grant URC NCC NNX08BA44A
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