A CFD based Numerical Analysis of Scramjet Combustor

Abstract

A CFD based modeling of flow phenomena in a modified DLR scramjet combustor has been performed. To enhance the air fuel mixing and to increase the combustion efficiency at the expense of low stagnation pressure drop, internal passages are provided in the wedge shaped strut fuel injector. Two-dimensional RANS equations are solved considering the flow to be steady, compressible, turbulent and reacting. A single step reaction is considered for hydrogen-oxygen reaction. A combination of eddy dissipation and finite rate chemistry models are used. The effects of divergence angle on the pressure drop and the combustion efficiency have been reported. A strut with internal passage shows higher combustion efficiency with less pressure drop than that without passages.