大推力氢氧火箭发动机液氢多级泵仿真与试验  

Simulation and Experiment for Multistage Liquid Hydrogen Pump of Large Thrust Hydrogen-oxygen Rocket Engine

作　　者：安阳[1] 陈聿晨 金志磊 林奇燕[1] 孙纪国 An Yang;Chen Yu-chen;Jin Zhi-lei;Lin Qi-yan;Sun Ji-guo(Beijing Aerospace Propulsion Institute,Beijing,100076)

机构地区：[1]北京航天动力研究所,北京100076

出　　处：《导弹与航天运载技术》2020年第4期45-50,共6页Missiles and Space Vehicles

摘　　要：作为火箭发动机的心脏,高效高扬程液氢多级泵的研制具有重要意义。对一种包括高效高扬程离心叶轮、低损失级间流道及进出口壳体的液氢多级泵进行研究,通过CFD对整个流体域进行仿真,并采用水力试验进行验证,分析了该泵的水力性能和汽蚀性能,验证了该泵设计合理,能够满足大推力氢氧火箭发动机使用需求。As the heart of the rocket engine, the development of high-efficiency high-lift liquid hydrogen multi-stage pump is of great significance. A liquid-hydrogen multi-stage pump is studied, including high-efficiency high-range centrifugal impeller, low-loss interstage crossover and suction casing and outlet housing, the whole fluid domain is simulated by CFD, and verified by hydraulic test, its hydraulic and cavitation properties are analyzed, and it is verified that the pump is reasonably designed, and it can meet the demand of high-thrust hydrogen-oxygen rocket engine.

关 键 词：液氢多级泵 仿真分析 水力试验 水力性能 汽蚀性能 

分 类 号：V434[航空宇航科学与技术—航空宇航推进理论与工程]