Numerical Investigation on Hydrogen-Fueled Scramjet Combustor with Parallel Strut Fuel Injector at a Flight Mach Number of 6

A numerical analysis of the inlet-combustor interaction and flow structure through a scramjet engine at a flight Mach number M = 6 with parallel injection (Strut with circular inlet) is presented in the present research article. Three different angles of attack ([alpha]=-4[degrees], [alpha]=0[degree...

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Bibliographic Details
Published in:Journal of Applied Fluid Mechanics 2016, Vol.9 (3), p.1215-1220
Main Authors: Pandey, Krishna, Roga, Sukanta, Choubey, Gautam
Format: Article
Language:English
Subjects:
Angle of attack
Circularity
Combustion
Combustion chambers
Configurations
Flight
Fuel injection
Injection
Injectors
Mach number
Mathematical models
Numerical analysis
Scramjet engines
Scramjet
Hypersonic Combustion
k−ε Realizable model
Parallel injector
Scramjets
Struts
Supersonic aircraft
Supersonic combustion ramjet engines
Supersonic speed
Vorticity
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Summary:A numerical analysis of the inlet-combustor interaction and flow structure through a scramjet engine at a flight Mach number M = 6 with parallel injection (Strut with circular inlet) is presented in the present research article. Three different angles of attack ([alpha]=-4[degrees], [alpha]=0[degrees], [alpha]=4[degrees]) have been studied for parallel injection. The scramjet configuration used here is a modified version of DLR scramjet model. Fuel is injected at supersonic speed (M=2) through a parallel strut injector. For parallel injection, the shape of the strut is chosen in a way to produce strong stream wise vorticity and thus to enhance the hydrogen/air mixing inside the combustor. These numerical simulations are aimed to study the flow structure, supersonic mixing, and combustion phenomena for the three different types of geometries along with circular shaped strut configuration.
ISSN:1735-3572
1735-3645
DOI:10.18869/acadpub.jafm.68.228.24082