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

编制了火箭发动机导向器/泵内低温两相流叶栅的数值计算程序。均匀混合模型得到了广泛的应用，采用三维有限体积法对欧拉型基本方程的对流项采用TVD格式，并考虑了气液之间的非平衡相变，编制了主程序。计算结果表明，由于空泡对声速的影响，两相流很容易变成超音速，导致入口气流进入叶栅的唯一入射条件，并导致压头下降。有趣的是，非平衡相变倾向于降低两相流的压缩效应，而三维效应在某种程度上放松了唯一的入射限制来恢复压头。应用所开发的程序与现有的实验观测结果进行比较，从而建立起更好的软件包，作为研究低温先进火箭发动机引进器/泵性能改进的数据库，似乎是很有前途的。

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.