Effects of Combustion and Shock Impingement on Supersonic Film Cooling by Hydrogen

Supersonic e lm cooling with H 2 coolant was numerically investigated by considering the combustion of the coolantandtheimpingementoftheshockwave.Theine uenceoftemperaturee uctuationwasincludedincalculating chemical rate constants. The combustion region was formed apart from the wall, and there was little heat release from thee ame.Therefore, thecombustion ofH 2 hadonlya weak ine uenceon thecharacteristicsofthee lm cooling. Thelocationofignition movedupstreamconsiderablydueto thetemperaturee uctuations. However,themovement decreased the cooling efe ciency very slightly. In addition, the effect of shock impingement on the e lm cooling by reactive H2 was almost the same as that of nonreactive N 2 with the same coolant injection Mach number. Nomenclature A = Jacobian matrix a = sonic velocity, m/s C = mole fraction c = constants d = height of coolant injector, m E = vectors of convective e uxes in the n direction Ev = vectors of viscous e uxes in the n direction F = vectors of convective e uxes in the g direction Fv = vectors of viscous e uxes in the g direction