超音速燃烧二元流场的数值模拟

A NUMERICAL ANALYSIS OF TWO DIMENSIONAL SUPERSONIC AIR FLOW

关键词:  冲压喷气发动机  超音速燃烧  二元流  流动分布  数值解

Key words:  Ramjet  Supersonic combustion  Binary fluid  Flow distribution  Numerical solution

摘要:

由二元超音速燃烧流场垂直喷射Ｈ＿２的数值模拟计算，描述了缝隙喷嘴附近氢气与空气的混合和燃烧过程。使用两步化学反应、ＭａｃＣｏｒｍａｒｋ显式时间分裂法和Ｂａｌｄｗｉｎ－Ｌｏｍａｘ修正的代数湍流模型，计算超音速燃烧流场，得出了流线、静压、静温、Ｈ＿２和Ｈ＿２Ｏ浓度等值线图，反映了缝隙喷嘴附近回流区的大小、自动着火点的位置及火焰向主流的传播现象。

Abstract:

A two-dimensional supersonic combustion flowfield is numerically simulated to under,tand the phenomena and mechanism of mixing and combustion processes near a slot injector injecting hydrogen transversely in a scramjet enging. A two-step global model is applied to the calculation of hydrogen-fueled turbulent combustion in supersonic airstream. Results are presented, which show the streamlines, the contours of static pressure and static temperature, and the concentrations of H2 and H2O, and also describe the size of seperation zones near the injector, the locations where autoignition occurs, and how flames propagate into the airstream.