固体火箭技术2011，Vol.34Issue(6)：707-710,4.
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
吴限德 1张斌 2陈卫东 1夏广庆 3陈茂林2
作者信息
- 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
- 折叠
摘要
Abstract
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.关键词
固体火箭发动机/喷管/气粒两相流动/CFD/DSMCKey words
solid rocket motor/nozzle/gas-particle two-phase flow/CFD/DSMC分类
航空航天引用本文复制引用
吴限德,张斌,陈卫东,夏广庆,陈茂林..固体火箭发动机喷管内气粒两相流动的CFD-DSMC模拟[J].固体火箭技术,2011,34(6):707-710,4.
