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

• 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

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

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

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

Determination of Mach Speed

• Calculations

• Schlieren Imaging– Cold flow

– Analyze shock wave profiles

Schlieren Imaging

• Acrylic chamber– Allows visualization

– H Studios Haziza polishing

• Schlieren Imaging– Cold flow

– Analyze shock wave profiles

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

Schlieren Imaging

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• Best Picture

OverexpandedPressure at nozzle exit lower than ambient

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

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

Thanks!!

• Kalind Carpenter

• Ramiro Galicia

Any Questions?

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

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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