combustion team supersonic combustion 6/14/20151nasa grant urc ncc nnx08ba44a faculty advisors: dr....
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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:
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Outline
• Background
• Determination of Supersonic Flow– Schlieren system
– Transparent (acrylic) Chamber
– Cold Flow
• FLUENT Analyses
• Refuel Hydrogen Tank
• Large Compressor
• Incorporate setup – From miniature chamber
– To wind tunnel
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Background
• Scramjet– Main form of combustion is supersonic
• Hypersonic flight
• Space travel
• Circumnavigation
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Background
• Scramjet engine works at supersonic speeds
• Goal - Design and maintain supersonic combustion in combustor
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Mach 5 Mach 3 Mach 5
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Standard Thrust Calculations
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• Micro Nozzle
• Throat Area = 0.01 ft2
• Exit / Throat Area = 2.0
• Entrance / Throat Area = 5.76
• Thrust = 104 lbs
• Hyper-X Approximation
• Throat Area = 1.0 ft2
• Exit / Throat Area = 2.0
• Entrance / Throat Area = 5.76
• Thrust = 10,479 lbs
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Miniature Nozzle Modifications
• Small scale nozzle
• Need to calculate discharge coefficient– Boundary layer interaction
– Affects mass flow rate
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Miniature Nozzle Calculations
• Discharge Coefficient
• ASME Tables
• Thrust
• Built thrust plate to compare experimental values
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Test Parameters
• Engine Application
• Operating Parameters– 134 psi Air
– 200 psi Hydrogen
• Air Velocity Perspective– Air inside ~ 2.5 Mach
– Air outside
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Determination of Mach Speed
• Calculations
• Schlieren Imaging– Cold flow
– Analyze shock wave profiles
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Schlieren Imaging
• Acrylic chamber– Allows visualization
– H Studios Haziza polishing
• Schlieren Imaging– Cold flow
– Analyze shock wave profiles
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Schlieren System
• Built platform for wind tunnel
• Three Schlieren cases– Nozzle alone
– Constant area chamber section
– Large diameter chamber section
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Possible Results
OverexpandedPressure at nozzle exit lower than ambient
UnderexpandedExit pressure greater than back pressure
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Schlieren Imaging
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• Best Picture
OverexpandedPressure at nozzle exit lower than ambient
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FLUENT Results
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Wind Tunnel Modifications
• Transfer miniature chamber setup to wind tunnel
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Refuel Hydrogen Tank
• Ordered!
• Arrives by Friday
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Testing
• Improve testing capabilities
• Thrust measurements– Force transducers
• Wind tunnel incorporations
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Future Work
• Schlieren setup and imaging
• Purchase compressor
• More Testing
• NASA Report
• USC Fluids Conference
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Thanks!!
• Kalind Carpenter
• Ramiro Galicia
Any Questions?
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Timeline2011
Hypersonic Combustion Team Timeline: March 2011 - June2011
2011
Student Name March April May June
Sara Esparza
Finish fabrication of combustion chamber
Schlieren Photography Setup & Analysis
Test Intake with Hydrogen
Publish Papers
Test Full Thrust System inWind TunnelFluent analysis of hydrogen and air
inside intake mixtureDetermine the possibility of
premixing hydrogen
Cesar Olmedo
Finish fabrication of combustion chamber
FinalizeSpark
System andStrength
SchlierenPhotography
SetupTest Intake with
Hydrogen
Publish Papers
Test Full Thrust System inWind Tunnel
Fluent analysis of combustion chamber
10//2009 NASA Grant URC NCC NNX08BA44A
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04/18/23 NASA 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. 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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04/18/23 NASA 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”. 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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