Combustion TeamHigh Speed 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:

Purpose

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

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Converging-Diverging Nozzle

• Nozzle brings air up to speed

• Entry and exit nozzle views

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CD Nozzle Drawing

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CD Nozzle Calculations

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86.2

413.

422.

2

2

Expansion Area Ratio

Throat

Compression Area Ratio

Expansion Area Ratio

Throat Area

Expansion Area Ratio A

AM = 2.4

Isentropic flow properties

D=.30D=.22

2.86

Throat D= .13

Nozzle Data

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Initial Testing

• Tested nozzle design

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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

Numerical and Experimental Results Coincide

• Exit pressure corresponds to 5.23 psia as seen in testing

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Nozzle Error

• 22% Error between Experimental and Numerical Calculations

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%22%100*73.6

23.573.6

P

)P - (P

alexperiment

ltheoreticaalexperiment

Testing

• Picture of the set up

• Used hydrogen tank from MFDCLab

• Combustion occurred

• Below Mach one

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Mixing Cavity & Combustor

• Initial Concept– Use cavity to re-circulate fuel

and air improve mixing

– Produce ideal combustion environment

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Ignition System

• Car distributor

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Overall Design

04/18/23 NASA Grant URC NCC NNX08BA44A

Lab Supply Quick Release – CD Nozzle ConnectionSection View

Fuel inlet

Fuel inlet

Testing Results

• We developed combustion

• Flow speed was not supersonic

• Cavity was too big and it produced a bow shock and reduced flow

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Final Design

• Met with Dr Wu to develop

• Smaller cavity

• Development of hydrogen and spark plug manifold

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Pathlines and Particle Tracing

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Final Design

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Final Design

• Solidworks assembly

• Side and front views

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Future Work

• Test at supersonic speeds

• Incorporate heating coil

• Add insulation

• Acquire silane

• Purchase Gambit or ICES

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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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