Supersonic combustion of scramjet jet cavity with ramp; computational studies using LES

Fuel injection schemes impact the combustion efficiency, flame stability and thermoacoustic instabilities in supersonic combustion. Usually, the fuel injection can be upstream or downstream the cavity. The present studies concerns the effect of the fuel injection scheme, upstream/downstream, on the combustion instabilities and efficiency in supersonic combustion. The combustion efficiency is assessed based on the turbulent mixing and temperature inside the cavity. Due to the fact that the experimental studies of supersonic combustion poses significant challenges. Therefore, computational approaches are a promising alternative for the numerical studies of supersonic combustion. In the present study the computations are performed using the large-eddy simulation approach along with a flamlet combustion model. The analysis reveals the presence of a region of high level of temperature, NO and 2 CO , inside the cavity. The reverse flow causes a preferential distribution of this region towards the step side of the cavity.