G0600303 The effect of equivalence ratio on supersonic combustion using streamwise vortices induced by a strut injector

Abstract

This paper presents a numerical simulation study of the supersonic combustion at Mach number 2.48. Hydrogen fuel is injected into a combustor at sonic speed from the rear of hyper-mixer strut that can generate streamwise vortices. Although, for equivalence ratio 0.4, hydrogen is well consumed, it remains partly as unburned fuel for equivalence ratio 1.0. The property shows that the amount of combustion is saturated at equivalence ratios over 0.4, although there is a slight increase beyond 1.