固体火箭发动机喷管两相流动计算

Calculation of Two Phase Flow for Solid Rocket Motor Nozzle

采用MacCormark格式与特征线法联合的方法求解了固体火箭发动机喷管两相流场。在跨音速段,气相控制方程用基于MacCormark格式的时间相关法求解,粒子方程采用跟踪粒子轨迹的特征线法求解;在超音速段,气相控制方程用MacCormark两步显格式空间步进求解,粒子方程仍采用跟踪粒子轨迹的特征线法求解,两相充分偶合。在控制方程中考虑了三氧化二铝颗粒的相变。最后对JPL喷管进行了计算,并讨论了不同质量分数对流场的影响。

A method which combines MacCormark scheme with the characteristic line method is used to calculate the two phase flow in solid rocket motor nozzle. In transonic region, the gas-phase governing equations are solved by time-dependent method based on MacCormark explicit scheme, while the partical equations by the characteristic line method following the tracks of particles. In supersonic region, the gas-phase governing equations are solved by space-marching MacCormark explicit scheme, while the partical equations also by the characteristic line method. Gas-phase and partical-phase are fully coupled. The phase change of A12O3 partical is taken into account in the governing equation. At last, the JPL nozzle two phase flow is calculated and the effects of different partical mass fractions is discussed.