Numerical Analysis of Hypersonic Combustion of a Scramjet Combustor with a Central lobed Strut Injector at Flight Mach Number 7
K.M Pandey1, Gautam Choubey2
1Dr. K.M Pandey, Department of Mechanical Engineering, NIT Silchar (Assam), India.
2Gautam Choubey, M.Tech, Department of Thermal Engineering, Mechanical Engineering, N.I.T Silchar (Assam), India.
Manuscript received on 13 February 2014 | Revised Manuscript received on 20 February 2014 | Manuscript Published on 28 February 2014 | PP: 52-58 | Volume-3 Issue-9, February 2014 | Retrieval Number: I1474023914/14©BEIESP
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Abstract: A numerical study of the inlet-combustor interaction and flow structure through a scramjet engine at a flight Mach number M = 7(Hypersonic Combustion) is presented. The scramjet configuration incorporates an inlet with an 8 degree compression ramp, followed by an isolator, and a divergent combustor. Fuel is injected at supersonic speed (M=2) through a central strut injector. The shape of the strut is chosen in a way to produce strong stream wise vorticity and thus to enhance the hydrogen/air mixing. To investigate the influence of the central injector on the flow behavior, reacting cases have been studied. For the reacting cases, the shock wave pattern is modified due to the strong heat release during combustion process. The shock structure and combustion phenomenon are not only affected by the geometry, but also by the flight Mach number and the trajectory. The k-ε realizable computations are capable of predicting mixing and combustion simulations well and good. For all reacting cases, fuel-air stoichiometric conditions are used.
Keywords: Scramjet, Hypersonic Combustion, k-ε Realizable Model, Flameholder.
Scope of the Article: Machine Design