摘要
将固体火箭发动机燃烧室和喷管作为一个整体，应用时间相关法进行了轴对称两相流场的一体化数值模拟。对气相采用ＭａｃＣｏｒｍａｃｋ显式差分格式，对颗粒相则采用特征线法进行计算。计算结果表明该方法可以对带潜入式喷管的发动机内复杂的两相流场进行有效的数值模拟。
he chamber and nozzle flow in solid rocket motor is considered as integrated.A timedependent numerical method is utilized for the calculation of two-dimensional,two-phase flows.Thetime-dependent compressible inviscid Euler equations for gas Phase are solved with an explicit MaoCormack scheme.For the particle phase with multiple sizes,the steady hyperbolic equations are solveby the method of characteristics with a predictor-corrector algorithm.The results show that thepresent method can be used to calculation the two-phase flow in the solid rocket motor withsubmerged nozzle.
出处
《推进技术》
EI
CAS
CSCD
北大核心
1996年第5期23-27,共5页
Journal of Propulsion Technology
关键词
固体推进剂
火箭发动机
流场模拟
数值模拟
Solid Propellant rocket engine,Insert nozzle,Two phase flow,Numericalsimulation,Flow field simulation
