Abstract
An experimental investigation of a Mach 2 combustor has been conducted in order to characterize flowproperties in a supersonic reacting flowfield. Hydrogen was injected transversely as staged, underexpanded jets behind a rearward facing step into a ducted Mach 2 air free stream. The effects of the chemical reaction on the supersonic flowfield was investigated using shadowgraphs, broadband flame emission photography, and planar laser-induced fluorescence of OH. The shadowgraphs indicated a strong affect of the heat release on the wave pattern in the combustor, with a significant increase in flowfield unsteadiness. The broadband flame emission photographs revealed large regions of no combustion in the vicinityof the fuel injectors where fuellair mixing was insufficient to support combustion. These regions decreased in size as the free stream stagnation temperature was decreased for fixed hydrogen mass flow rate, consistent with an increase in the effective Q-ratio with combustion. The size of the zones containing OH in the planar fluorescence images also both increased as the main flow stagnation temperature was decreased. Reaction zones were found in the planar fluorescence images away from regions containing injectant in a non-reacting study of the same geometry, indicating that the pressure rise associated with the reaction forced a large redistribution of the fuel.
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