关键词: 超音速燃烧;冲压喷气发动机;非定常流;数值模拟

Abstract: The processes of auto-ignition and combustion in supersonic air flow I with transverse hydrogen injection were calculated by means of the solution of two-dimensional N-S equations,using an algebraic eddy-viscosity model,a two-step global chemical model and MacCormack explicit timesplit method.The results stated clearly the variation of static temperature,static pressure,velocity and fuel-air equivalent ratio in the process from hydrogen injection,flame propagation to steadily combustion.The results also indicated that auto-ignition could occur in the thermal boundary layer and recirculation zone ahead of injector,and the static temperature of inlet air flow is a decisive factor which ef feets flame propagating from recirculation zone to turbulent mixing layer between air stream and hydrogen stream.The hydrogen stream in field behind injector is parallel to air flow,and there is strong turbulent mixing and reacting layer between them.Supersonic combustion efficiency is decided mainly by the mixing efficiency of these two streams.

Key words: Supersonic combustion;Ramjet engine;Unsteady flow;Numerical simulation