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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.
Based on Pierce low Mach number flame surface / progress variable model, considering the compressibility and the impact of shock wave, a flame surface / progress variable model for supersonic turbulent flow was developed. By solving the mixed fraction and the progress variable Two scalar equations are used to describe the chemical reaction, and the complete three branches of the flame surface equation are solved: the steady-state combustion branch, the unsteady branch with the partial flameout state and the complete flameout branch.This model is applied to the German Aerospace Center (DLR ) Scramjet was simulated, which was different from that of the steady-state flame model. The results of the calculation captured the phenomenon of flameout and flame lift; and the numerical shadow and average temperature distribution were in good agreement with the experimental results.