超声速反应流火焰面/进度变量模型

基于Pierce低马赫数条件下的火焰面/进度变量模型,考虑可压缩性和激波的影响,发展了用于超声速湍流反应流的火焰面/进度变量模型.该模型通过求解混合分数和进度变量两个标量方程来描述化学反应,且采用火焰面方程解的完整的三个分支：稳态燃烧分支、具有局部熄火状态的非稳态分支和完全熄火分支.利用该模型对德国宇航中心（DLR）的超燃冲压发动机进行模拟,与稳态火焰面模型得到的附着火焰不同,计算结果捕捉到了熄火和火焰抬举现象;且数值阴影和平均温度分布与实验结果吻合较好.

Flamelet/progress variable model for supersonic reacting flows

The flamelet/progress variable model for supersonic turbulent reacting flows was developed based on Pierce's model for low Mach number flows,in consideration of the compressibility effects and shock waves.The present model solved the mixture fraction and progress variable transport equations,and employed three solution branches of flamelet equation:the steady burning branch,the unstable branch of partially extinguished states and the complete extinction state.The performance of the flame/progress variable model was compared to the steady flamelet model for predicting the product and temperature field of a hydrogen-air supersonic combustion ramjet engine in DLR (Deutsches Zentrum für Luft- und Raumfahrt) for which experimental data are available.With capturing of extinction and lifted flame,the present model is good agreement with the experimental data,and outperforms the steady flamelet model which predicts an attached flame.