Abstract: For computation of the flow field established in the chamber of solid liquid rocket ramjet,the block implicit algorithm was used to solve the Navier Stokes equations for gas.The separated flow model and continuum formulation model were used to characterize the flow and vaporization of droplets.For droplet flow,a special approach was tried to represent the law of mass conservation and the size changing of the droplets.It was demonstrated that the solution was rapidly convergent and the numerical results were qualitatively correct.

Key words: Lithergol rocket engine;Rocket ramjet;Afterburner;Flow distribution;Two phase flow

摘要： 为了计算固液混合式火箭冲压发动机补燃室内带有燃料液滴的流场 ,用块隐式法计算气相流场 ,用分离流连续介质模型计算颗粒相的流动与蒸发过程 ,在控制方程组的联合求解中 ,采用特定的算法来体现颗粒相的质量守恒律与尺寸的变化。算例表明 ,迭代过程能够快速收敛 ,计算结果定性正确。

关键词: 液固混合火箭发动机;火箭冲压发动机;加力燃烧室;流动分布;二相流