固体火箭发动机内轴对称两相流场的一体化数值模拟

推进技术 ›› 1996, Vol. 17 ›› Issue (5): 23-27.

固体火箭发动机内轴对称两相流场的一体化数值模拟

夏智勋,丁英仁,方丁酉,张为华

国防科技大学航天技术系;国防科技大学航天技术系;国防科技大学航天技术系;国防科技大学航天技术系

发布日期:2021-08-15

CALCULATION OF TWO-PHASE INTERNAL FLOWIN SOLID ROCKET MOTOR

Dept.of Aerospace Technology,National Univ.of Defense Technology,Changsha,410073;Dept.of Aerospace Technology,National Univ.of Defense Technology,Changsha,410073;Dept.of Aerospace Technology,National Univ.of Defense Technology,Changsha,410073;Dept.of Aerospace Technology,National Univ.of Defense Technology,Changsha,410073

Published:2021-08-15

摘要/Abstract

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。

关键词: 固体推进剂火箭发动机;潜入式喷管;二相流;流场模拟;数值模拟

Abstract: 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.

Key words: Solid Propellant rocket engine;Insert nozzle;Two phase flow;Numericalsimulation;Flow field simulation

夏智勋,丁英仁,方丁酉,张为华. 固体火箭发动机内轴对称两相流场的一体化数值模拟[J]. 推进技术, 1996, 17(5): 23-27.