Development of Software Database for Advanced Cascade Design in Rocket Engine Turbopumps

本文编制了火箭发动机诱导轮/泵低温两相流叶栅设计与分析的数值程序，由于均质混合物模型的广泛应用，主程序采用三维有限体积法，对Euler型基本方程的对流项采用TVD格式，计算结果表明，这两种方法都能较好地考虑汽液两相间的非平衡相变。由于空隙对声速的影响，相流很容易变为超声速，导致进口气流进入叶栅的唯一冲角条件，导致其压头降低。有趣的是，发现非平衡相变倾向于降低两相流的可压缩性效应，并且三维效应在某种程度上放松了独特的冲角限制以恢复压头。从而建立更好的软件包作为处理低温先进火箭发动机诱导轮/泵的改进性能的数据库。

Numerical codes for design and analysis problems of cryogenic two-phase flow cascades in rocket engine inducer/pumps have been programd.Homogeneous Mixture Model has been extensively applied, so that the principal code was formulated by 3D Finite Volume Method adopting TVD scheme for the convection terms of the Euler type basic equations, which allowed to take into consideration of unequilibrium phase chage between vapor and liquid.Calculation results by using those codes showed that the two-phase flow would easily become supersonic due to the void effect upon sound velocity which lead to the unique incidence condition for the inlet flow into the cascade and caused the decrease in its pressure head. It was interesting as well to find that the unequilibrium phase change tended to decrease the compressibility effect of two-phase flows and that the 3D effects somehow relaxd the unique incidence restriction to recover the pressure head.It seems quite promising to apply the developed codes for comparing with the existing experimental observations, thus establishing the better software package as a database that treats the improved performance of cryogenic advanced rocket engine inducer/pumps.