Abstract

Understanding the scramjet combustion and significant effect of each parameter is very much important for the design and analysis. The computational analysis has been carried out by using the commercial software FLUENT. The 3D, Steady, Compressible reacting flow has been simulated using k-epsilon turbulence model, species transport combustion model and finite rate/eddy dissipation model for reacting flow. The scramjet combustor selected is same as the combustor at DLR institute for space propulsion. The H2 fuel is injected through the strut at its center. The operating conditions used for the engine are Mach number 2, and the mass flow rate of the hydrogen from the injector is 0.004 kg/s. The computational results obtained from the analysis have been validated and the effect of Mach number has been systematically studied with the help of static pressure and static temperature in the combustor. The physics of the flow field in combustor such as mixing, atomization, combustion has been captured by Mach, temperature and pressure contours.

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