液体火箭发动机涡轮气动优化数值研究
于 晴1,赵 慧2,袁伟为1,李爱民1,张亚太1

(1.西安航天动力研究所,陕西 西安 710100; 2.火箭军装备部装备项目管理中心,北京 100085)

液体火箭发动机; 涡轮; 面积比; 气动优化

Numerical study on aerodynamic optimization of liquid rocket engine turbine
YU Qing1,ZHAO Hui2,YUAN Weiwei1,LI Aimin1,ZHANG Yatai1

(1.Xi'an Aerospace Propulsion Institute,Xi'an 710100,China; 2.The Equipment Project Management Center of the Rocket Army, Beijing 100085, China)

liquid rocket engine; turbine; area ratio; aerodynamic optimization

备注

在某型液体火箭发动机研制中,为了使氧预压涡轮泵中驱动涡轮的燃气与主路中的液氧完全掺混、冷凝,需要尽可能地提高涡轮效率。采用并行多目标气动优化设计软件,以自适应多目标差分进化算法为优化工具对氧预压涡轮泵叶栅进行优化设计。计算结果表明:涡轮各级优化设计后,内部流动损失减小,整机效率提高了3.739%; 涡轮转子两列动叶的最大应力均小于材料的屈服强度,满足强度要求; 涡轮叶栅采用并行多目标气动优化方法进行优化,降低了燃气比例,有利于火箭发动机氧预压涡轮泵中燃气的更好溶解。

During the development of a liquid rocket engine, in order to completely mix and condense the gas driving the turbine in the oxygen pre-pressurized turbo pump with the liquid oxygen in the main circuit, it is necessary to improve the turbine performance as much as possible.In this paper, the parallel multi-objective aerodynamic optimization design software was used to optimize the cascade design of the oxygen pre-pressurized turbo pump with the adaptive multi-objective differential evolution algorithm as the optimization tool.The calculation results show that after the optimization design of the turbine, the internal flow loss is reduced and then the overall efficiency is increased by 3.739%.The maximum stress of the two stage blades of the turbine rotor is less than the yield strength of the material, which meets the strength requirements.The turbine cascade can be optimized by the parallel multi-objective aerodynamic optimization method, which reduces the gas ratio and is beneficial to the complete dissolution of gas in the oxygen pre-pressurized turbo pump of rocket engine.