预压涡轮泵轴流式液力涡轮的流动结构研究  

Research on the Flow Structure in the Axial Hydraulic Turbine of the Boost Turbopump

作　　者：廖懂华 林奇燕[1] 叶小明[1] Liao Dong-hua;Lin Qi-yan;Ye Xiao-ming(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》2018年第6期49-54,共6页Missiles and Space Vehicles

摘　　要：高压补燃氢氧火箭发动机采用预压泵技术能有效提高推进剂泵的抗汽蚀性能,并大大减轻火箭贮箱的重量。氧预压泵一般通过轴流式液力涡轮驱动。采用数值方法对美国航天飞机主发动机所采用的多级轴流式液力涡轮的内部流场进行仿真计算,通过对马蹄涡、通道涡、泄漏涡等涡系结构的分析,研究了二次流对主流的影响,以及二次流造成的总压损失在叶栅通道中的分布情况。研究结果表明:马蹄涡会加强通道涡,泄漏涡在叶尖吸力侧下游形成,3种涡系结构深刻影响叶栅通道流动,产生较大的总压损失。For high pressure hydrogen/oxygen staged combustion rocket engine,boost turbopump technology can effectively improve the anti-cavitation performance of propellant pump and reduce the weight of rocket propellant tanks.The oxygen boost turbopump is usually driven by an axial hydraulic turbine.The inner flow field of the multistage axial hydraulic turbine of the space shuttle main engine is studied by numerical method.By analyzing the structure of vortexes,such as horseshoe vortex,passage vortex and leakage vortex,the effect of secondary flow on main flow field and the distribution of total pressure loss resulted from secondary flow are also studied.The results show:the horseshoe vortex could strengthen the passage vortex,the leakage vortex forms in the downstream near the suction side of the blade tip;those vortexes have a profound effect upon the cascade flow and lead to great total pressure loss.

关 键 词：氢氧火箭发动机 预压涡轮泵 轴流式液力涡轮 二次流 

分 类 号：V434[航空宇航科学与技术—航空宇航推进理论与工程]