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用三维湍流Ｎ－Ｓ方程及拟流体模型描述液体火箭发动机内部喷雾两相燃烧流动过程，两相之间的质量交换采用蒸发模型计算，气相化学反应速率采用Ａｒｒｈｅｎｉｕｓ公式计算。采用ＳＩＭＰＬＥＲ与ＩＰＳＡ算法求解两相控制方程并对氢氧发动机燃烧流动过程进行了三维数值分析，得到了发动机推力室内燃气参数的详细分布情况。结果表明对氢氧发动机而言，蒸发过程非常快，推进剂混合过程是燃烧过程的决定因素。
The three-dimensional turbulent N-S equation and the quasi-fluid model are used to describe the internal combustion two-phase combustion flow in a liquid rocket engine. The mass exchange between two phases is calculated by the evaporation model. The gas phase chemical reaction rate is calculated by Arrhenius formula. The SIMPLER and IPSA algorithms were used to solve the two-phase control equations and the three-dimensional numerical analysis of the oxyhydrogen engine combustion process was carried out. The detailed distribution of the indoor gas parameters of the engine thrust was obtained. The results show that for the oxyhydrogen engine, the evaporation process is very fast and the propellant mixing process is a decisive factor in the combustion process.