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建立了任意斜交曲线坐标系下液体火箭发动机（ＬＲＥ）内部工作过程的气液两相湍流化学反应流模型。应用该模型对气氢液氧模型燃烧室内部燃烧过程进行了数值模拟，得到了全流场的速度分布图形、燃气组分等值线、流场等温线、流场等压线、流场等马赫数线、壁面温度与径向平均温度曲线和燃烧效率曲线。计算结果表明：用数值模拟方法分析ＬＲＥ内部工作过程是可行的。
The gas-liquid two-phase turbulent chemical reaction flow model for the internal working process of a liquid propellant rocket engine (LRE) under any bias curve coordinate system was established. The model was used to simulate the combustion process inside the combustion chamber of a gas-liquid hydrogen-oxygen model. The velocity profile, the gas component contour, the flow field isotherm, the flow field isobar and flow fields were obtained Mach number line, wall temperature and radial average temperature curve and combustion efficiency curve. The results show that it is feasible to analyze the internal working process of LRE by numerical simulation.