氢氧发动机氢涡轮泵汽蚀试验技术研究  

Study on the Turbo Pump Cavitation Test of Hydrogen and Oxygen Engine

作　　者：李培昌[1] 冯飞[1] 王建宇[1] Li Pei-chang;Feng Fei;Wang Jian-yu(Beijing Institute of Aerospace Testing Technology, Beijing, 100074)

机构地区：[1]北京航天试验技术研究所,北京100074

出　　处：《导弹与航天运载技术》2018年第6期55-58,共4页Missiles and Space Vehicles

摘　　要：针对氢氧发动机涡轮泵难以采用真实低温介质进行汽蚀试验的问题,提出在发动机试验过程中降低泵入口压力进行涡轮泵汽蚀试验的方法。采用数值模拟计算不同控制方式下发动机泵入口压力的变化趋势,确定了压力控制方法。经过试验验证,该压力控制方法可行,首次实现了人为控制的氢涡轮泵汽蚀试验,获取了氢涡轮泵的实际汽蚀点,为发动机氢涡轮泵的抗汽蚀性能研究提供了重要技术数据。To solve the problem that the cavitation test of the turbo pump of hydrogen and oxygen engine are difficult to carry out with real cryogenic medium,a new method of reducing the pump inlet pressure in the turbo pump cavitation test is put forward in this study.The change tendency of the inlet pressure of the engine pump under different control modes is calculated by numerical simulation,so the method of pressure control is determined.The experimental results show that the method of pressure control is feasible,the aitificially-controlled cavitation test of the turbo pump is obtained for the first time,and the actual cavitation point is acquired,which provides the important technical data for the study of the anti-cavitation performance of the engine hydrogen turbo pump.

关 键 词：汽蚀试验 数值模拟 汽蚀点 

分 类 号：V434.3[航空宇航科学与技术—航空宇航推进理论与工程]