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

作　　者：吴限德[1] 张斌[2] 陈卫东[1] 夏广庆[3] 陈茂林[2] 

机构地区：[1]哈尔滨工程大学航天与建筑工程学院,哈尔滨150080 [2]西北工业大学燃烧流动和热结构国家级重点实验室,西安710072 [3]大连理工大学工业装备结构分析国家重点实验室航空航天学院,大连116024

出　　处：《固体火箭技术》2011年第6期707-710,共4页Journal of Solid Rocket Technology

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 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.

关 键 词：固体火箭发动机 喷管 气粒两相流动 CFD DSMC 

分 类 号：V435[航空宇航科学与技术—航空宇航推进理论与工程]