Abstract
Flame stabilization in a Ma=2.5 direct-connect supersonic combustor was experimentally characterized with a fixed stagnation pressure of 1.0MPa and wide ranges of stagnation temperature (T0) from 1200K to 1800K and global equivalence ratio (Φ) of ethylene/air from 0.1 to 0.8. Four typical flame stabilization modes were identified by using the time resolved CH* chemiluminescence and presented as a regime nomogram in the T0–Φ parameter space. As increasing T0, the range of Φ for the flame stabilization modes is widened and that for the oscillation mode is therefore narrowed. The widely used quasi-1D analysis, with the experimentally determined wall static pressure distribution as input parameters, suggests that the combustor operates in a scramjet mode when the flame is stabilized in the cavity shear layer and in a ramjet mode when the flame is in the jet-wake. The flame oscillation mode, observed only for a narrow range of Φ, was found to correlate with the combustor transition between the scramjet and ramjet modes.
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