预压涡轮泵轴流式液力涡轮的流动结构研究
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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.
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.
引文
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[2]Mahmood G I,Gustafson R,Acharya S.Experimental investigation of flow structure and nusselt number in a low-speed linear blade passage with and without leading-edge fillets[J].Journal of Heat Transfer,2005,127(5):499-512.
[3]Wang H P,Olson S J,Goldstein R J,Eckert E R J.Flow visualization in a linear turbine cascade of high performance turbine blades[J].Journal of Turbomachinery,1997,119(1):1-8.
[4]黄洪雁,韩万金,王仲奇.具有叶顶间隙涡轮转子叶栅流动的拓扑及旋涡结构观测[J].航空学报,1997,18(3):257-261.Huang Hongyan,Han Wanjin,Wang Zhongqi.Flow observation of topological and vortical structure in turbine rotor cascades with tip clearance[J].Acta Aeronautica Et Astronautica Sinica,1997,18(3):257-261.
[5]王仲奇,冯国泰,王松涛,陈乃兴.透平叶片中的二次流旋涡结构的研究[J].工程热物理学报,2002,23(5):553-556.Wang Zhongqi,Feng Guotai,Wang Songtao,Chen Naixing.Study on secondary flow vortex structures in turbine bladings[J].Journal of Engineering Thermophysics,2002,23(5):553-556.
[6]You D,Wang M,Moin P,Mittal R.Large-eddy simulation and analysis of tip clearance flows in turbomachinery applications[C].Proceedings of the2003 IEEE User Group Conference,2003.
[7]Pecnik R,Pieringer P,Sanz W.Numerical investigation of the secondary flow of a transonic turbine stage using various turbulence closures[R].GT2005-68754,2005.
[8]高杰,郑群,姜玉廷.涡轮间隙流动结构及其损失产生机理研究[J].工程热物理学报,2013,34(10):1833-1837.Gao Jie,Zhang Qun,Jiang Yuting.Investigation on tip clearance flow structure and its loss generation mechanism in turbine rotors[J].Journal of Engineering Thermophysics,2013,34(10):1833-1837.
[9]Boynton J L,Rohlik H E.Effect of tip clearance on performance of small axial hydraulic turbine[R].NASA-TM-X-3339,1976.