关键词: 超音速燃烧;数值仿真;超音速冲压喷气发动机

Abstract: The gas flow field in a simplified supersonic combustor with a slot hydrogen injector mounting behind strut and injecting hydrogen parallelly to air now is numerically simulated by using elliptical partial differential equation module and MacCormack scheme. The results show that there is a recirculation zone behind the strut. Pressure of injecting H2 higher than air flow and effects of boundary-layer lead to oblique shock wave and expansive wave in combustor, and pressure will take place great changes along transverse. It can be concluded that such flow field has an obvious difference from boundary-layer flow in performance. Thus, it is suggested that the whole flow field in supersonic combustor should be separately calculated according to its character. And then, the combustor performance could be obtained by integrating over the given nodes value (such as temperature, pressure). Compared with experimental data of reference [5], the simulated results are reasonable and reliable.

Key words: Supersonic combustion;Numrical simulation;Supersonic combustion ramjet engine