Abstract
Some general properties of a research-scale supersonic combustion device are reported and compared to a simple one-dimensional analysis of supersonic flow with heat addition and area change. The properties that were measured include the stagnation pressure losses because of combustion, the static pressure axial profiles, and the thermal choking limits; the heat-release pattern was inferred from these measurements. A simple combustor geometry was chosen that consists of a hydrogen-air turbulent jet flame that is stabilized along the axis of a supersonic (Mach 2.2) airflow within a diverging duct. It was found that the heat-release pattern (in kilowatts per centimeter of axial distance) is not uniform in space, but varies in a lognormal manner in the axial direction for the supersonic jet flame, which differs from the Gaussian pattern that characterizes a subsonic jet flame. The difference is attributed to earlier air entrainment and combustion caused by the supersonic coflowing air. It was found that it is possible to adequately estimate the measured stagnation pressure loss and the thermal choking limits using a one-dimensional analysis, if the measured lognormal shape of the heat release pattern is used. Measurements also quantify the wall divergence angle that is required to avoid thermal choking.
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