Computational investigation to study the effect of a hybrid hydrogen fuelled scramjet combustor on different inlet boundary conditions

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Supersonic Combustion ramjet or Scramjet is one of the revolutionary hypersonic innovations that use atmospheric oxygen to undergo the combustion process. For efficient combustion of the fuel different techniques are implemented in the combustor such as flame holding, fuel injection mechanism. A transverse fuel injection system is considered into which parallel fuel injection system is introduced, named as Hybrid scramjet combustor. In this paper, the influence of inlet Mach number on the performance of the hybrid combustor is analyzed. The current model is validated with an already available experimental study in the literature. Both graphical and qualitative analysis was done in the validation. The simulation results are in good agreement with the experimental study. In this study, static pressure contours shows the formation of oblique shock waves. The recirculation region is developed in the model due to the presence of parallel cavities. The temperature contours indicates the starting of combustion process. Due to the presence of strut in the parallel cavities increase the possibility of H2 injection in the combustion which improves the combustion process. The Mach number contours are studied for the different Mach numbers. The contours show the formation of an additional shock wave due to strut, as the Mach number increases the strength of the shock wave also increases. The recirculation region leads to the interaction of boundary layer and shock wave. The shear layer thickness is maximum for Mach number 3.0 and is minimum for Mach number = 2.25. The variation of static pressure for the different Mach number is covered in this paper. The static pressure values increases from the leading edge with the formation of oblique shock waves. This increase is due to the formation of reflected shock waves.