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本文应用数值模拟方法对液氢／液氧火箭发动机燃烧过程进行了计算，给出了发动机燃烧室内燃气参数分布。计算中通过随机喷雾模型确定液氧滴进入燃烧室的初始条件，应用高压蒸发模型计算液氧蒸发速率及Ａｒｒｈｅｎｉｕｓ公式计算氢氧气相化学反应速率。贴体网格由ＴＴＭ方法生成，数值方法采用一步隐式预测、两步显式校正的ＰＩＳＯ算法，控制方程在非交错网格下离散并且对流项采用了二阶迎风格式。
In this paper, the combustion process of liquid hydrogen / liquid oxygen rocket motor is calculated by numerical simulation, and the gas parameter distribution in the combustion chamber is given. In the calculation, the initial conditions of the liquid oxygen drop entering the combustion chamber are determined by a random spray model. The high-pressure evaporation model is used to calculate the rate of liquid oxygen vapor evolution and the Arrhenius formula to calculate the chemical reaction rates of hydrogen and oxygen. Body-fitted grids are generated by the TTM method. The numerical method uses one-step implicit prediction and PISO with two-step explicit correction. The governing equations are discretized under non-staggered grids and the second order upwind scheme is used for convection terms.