The heat-release ef ciency and the dynamics of thermal choking of a hydrogen-fueled supersonic combustor model have been evaluated in the low-speed ight regime characterized by Mach 3.75 ight enthalpy. The combustion chamber entrance Mach number, stagnation temperature, and combustor entrance Reynolds number were 1.56, 850 K and 1.2 million, respectively. The total equivalence ratio ranged to A = 0.7. A step- ameholding geometry was chosen to explore the effects of supersonic ow and high Reynolds number on normal bluff-body ame propagationand combustion ef ciency using direct fuel injection from the base. The combustorwas divided into two zones: a constant-area duct and an expanding section. The fuel was distributed in 1) the subsonic region formed in the base of the ameholder and 2) parallel to the main air ow in the core of streamwise vortices formed by the presence of ramps. In terms of fuel distribution, the split between the base and the ramp injectors over a range of total equivalence ratios indicated preference for the base injection at high total equivalence ratios. At modest total equivalence ratios no preferential fuel distribution among the injectors was found. Signi cant effects of compressibility and Reynolds number were found when compared to a reference experiment at low speed and low Reynolds number with the same step area ratio.
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Owens et al. (2001) studied this question.
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