固体火箭发动机喷管内气粒两相流动的CFD-DSMC模拟

摘要

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 particle 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.