Numerical Simulation of Combustion Chamber without Cavity at Mach 3 . 12

In this Simulation, supersonic combustion of hydrogen at Mach 3.12 has been presented. The combustor has a single fuel injection perpendicular to the main flow from the base. Finite rate chemistry model with K-ε model have been used for modeling of supersonic combustion. The pressure rise due to the combustion is not very high on account of global equivalence ratio being quite low. Within the inlet the shock-wave-boundarylayer interactions play a significant role. The combustor without cavity is found to enhance mixing and combustion while increasing the pressure loss, compared with the case without cavity to the experimental results. The OH mass fraction is less almost by an order to that of water mass fraction The OH mass fraction decreases as the gas expands around the injected jet and the local mixture temperature falls, However OH species are primarily produced in the hot separation region upstream of the jet exit and behind the bow shock and convected downstream with shear layer. The geometry results shows the better mixing in combustion chamber, caused by more extreme shear layers and stronger shocks are induced which leads loss in total pressure of the supersonic stream. Keywords— Hydrogen, Shear layers, Stabilization, stagnation temperature, Supersonic combustion,