固体火箭发动机喷管内气粒两相流动的CFD-DSMC模拟

Numerical simulation of gas-particle two-phase flow in SRM nozzle by the method of CFD-DSMC

气相采用Jameson中心差分格式和显式Runge-Kutta法求解可压缩的雷诺时均N-S方程,颗粒相采用DSMC方法描述,采用PSIC耦合算法模拟了JPL喷管中的气粒两相流动,得到了气相和颗粒相的参数分布规律。结果表明,流场中颗粒相含量越高,颗粒相对气相的阻碍和加热效应越显著,导致气相马赫数降低、温度升高;在相同颗粒含量的情况下,颗粒粒径越小,也能明显阻碍气相流动,同时对气相的加热效应也更显著;在颗粒确定性轨道模型计算下得到的无粒子区中,仍有少量非连续的颗粒存在。

The Reynolds Navier-Stokes equations were used to solve the gas-phase flow field by the methods of center difference scheme reported by Jameson and time-stepping explicit Runge-Kutta method. The distributions of gas-phase and particle-phase parameters were obtained. The particle-phase was described by the DSMC method. The gas-particle two-phase flow in JPL nozzle was solved by the method of PSIC. The results show that in the case of higher particle content, the gas-phase was more obviously impeded and heated by the particle-phase, resuting in the decrease of Mach number and increase of temperature. In the case of same par- ticle content, the same results were obtained by decreasing the size of particle. In the region without particles obtained by solving the deterministic model, there were a few of particles and the distribution of these particles was discontinuous.