Supersonic film cooling with H2 coolant was numerically investigated by considering the combustion of the coolant and the impingement of the shock wave. The influence of temperature fluctuation was included in calculating chemical rate constants. The combustion region was formed apart from the wall, and there was little heat release from the flame. Therefore, the combustion of H2 had only a weak influence on the characteristics of the film cooling. The location of ignition moved upstream considerably due to the temperature fluctuations. However, the movement decreased the cooling efficiency very slightly. In addition, the effect of shock impingement on the film cooling reactive H2 was almost the same as that of nonreactive N2 with the same coolant injection Mach number.
ASJC Scopus subject areas
- Aerospace Engineering