液氢/液氧火箭发动机燃烧过程二维数值模拟分析

NUMERICAL SIMULATION OF COMBUSTION PROCESS IN A LIQUID H_2/O_2 ROCKET ENGINE

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。

Numerical simulation is employed in calculation of the combustion processes in the rocket engine which uses liquid hydrogen and oxygen as propellants.A random spray model is used to describe the initial conditions of oxygen droplets.The evaporation rate of the oxygen droplets at high pressure is calculated by ZKS model.The Arrehnius model is adopted to compute the chemical reaction rates.PISO algorithm extended by the authors is used to calculate the spray combustion flow.The convection terms of the governing equations are discretized by a second-order upwind scheme.