摘要
采用欧拉-拉格朗日两相方法模拟了带长尾喷管的固体火箭发动机三维两相内流场。在同位网格基础上用有限体积法离散N-S方程,采用不完全LU分解预处理B iCGStab算法求解线性代数方程组,通过可压缩SIMPLE算法求解气相流场。用PSIC方法进行气粒耦合计算,得到了气粒两相的速度、温度等参数的分布以及不同尺寸的A l2O3粒子运动轨迹。计算结果表明,在发动机工作初期气粒两相流场呈现强三维特征,长尾管中后段、喷管收敛段以及燃烧室后封头等部位是烧蚀最严重的部位。
3D two-phase internal flow field of SRM with long-tail nozzle was simulated by means of Eulerian-Lagrangian twophase method. Based on coordinating grid, N-S equations were dispersed by means of finite volume method, and the linear algebraic equation set were solved by using Incomplete LU （ILU） factorization preconditioning BiConjugate Gradient Stabilized （BiCGStab） algorithm. Gas-phase flow filed was solved by compressible SIMPLE algorithm. PSIC method was used for gas-particle coupling calculation,and parameter distribution （velocity and temperature） of gas-particle two phases as well as trajectory of A1203 particles with different size were obtained. The calculation results show that gas-particle two-phase flow field presents strong 3D distribution feature at the beginning of motor working, and the middle-aft section of long-tail nozzle, convergence nozzle and aft dome are subjected to the most serious erosion.
出处
《固体火箭技术》
EI
CAS
CSCD
北大核心
2007年第3期205-209,共5页
Journal of Solid Rocket Technology
关键词
固体火箭发动机
两相流场
长尾喷管
数值模拟
solid rocket motor
two-phase flow field
long-tail nozzle
numerical simulation
