Abstract: The two dimensional,time dependent Navier Stokes equations were solved for supersonic flows of two parallel jets in a dual combustor.Numerical solution of these equations was accomplished with the flux split explicit finite difference algorithm of MacCormack.The Baldwin Lomax turbulent model was used for boundary flow and the mixing length model for shear layer.The numerical results are compared with experimental data,and the obtained results are better.Also the experiment shows that the effects of separation zone and the parameters of two supersonic flow jets on the wave pattern are significant.

Key words: Supersonic combustion ramjet engine;Daul combustor +;Supersonic combustion;Power plant;Numerical simulation

摘要： 采用Ｍａｃ Ｃｏｒｍ ａｃｋ 矢通分裂格式， 求解雷诺平均的Ｎ－Ｓ方程组， 采用Ｂａｌｄｗ ｉｎ－Ｌｏ－ｍ ａｘ 代数湍流模型和混合长度模型， 模拟超燃燃烧室内两股平行超声速来流的冷态流场， 取得了与试验相一致的结果， 计算表明回流区和射流流动参数对超燃燃烧室流场内波系的变化有着较大的影响。

关键词: 超声速冲压喷气发动机;双燃烧室;超音速燃速;动力装置;数值仿真