固体发动机喷管内两相流的有限元数值模拟  

FINITE ELEMENT NUMERICAL SIMULATION OF TWO-PHASE FLOW IN NOZZLE FOR SOLID ROCKET MOTOR

作　　者：姜贵庆[1] 王淑华[1] 王岩[1] 

机构地区：[1]北京空气动力研究所

出　　处：《空气动力学学报》1991年第1期58-66,共9页Acta Aerodynamica Sinica

摘　　要：本文给出了固体发动机喷管内两相流的数值模似。从非守恒型两相流甚本方程出发,采用加权积分技术,导出了离散点的流动物理量的有限元数值计算公式。数值模拟分别与JPL喷管的两相流壁面静压分布测量结果以及与差分法计算结果作了比较,比较结果表明:二者是吻合的。本文还以中型喷管为例,计算了粒子的轨迹,粒子的速度滞后和燃气的温度滞后,计算结果表明;入口粒子冲击角对粒子轨迹有明显的影响。Numerical simulations of two-phase flow in nozzle for solid rocket motor are presented in this paper. Starting from basic equation of two phase, using the weighted integral techniques, the numerical calculating formulations of flow physical parameters of discretization nodes by finite element method are provided. Numerical simulation of finite element method are compared with the experimental results of Mach number distribution for gas phase in JPL nozzle, with the measurement results of surface pressure for two phase flow in experimental nozzle and with the finite difference method respectively, The comparison results show a good agreement. For example, the particular trajectory, velocity lag of particles, temperaturs lag gas were calculated, it shows that the impact angle of particles in the entrance of nozzle has an important effect on particles trajectory.

关 键 词：喷管 两相流 火箭发动机 固体火箭 

分 类 号：V435.11[航空宇航科学与技术—航空宇航推进理论与工程]