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对一个用于大推力液体火箭发动机氧涡轮泵的复速级涡轮的喷嘴叶栅进行了试验研究 ,以考察喷嘴叶栅的气动特性 ,验证喷嘴叶栅的气动设计。该复速级喷嘴叶栅采用先进的后加载流动控制技术 ,以减弱叶栅的二次流损失。对喷嘴叶栅进行了四个进口气流角、三个出口等熵马赫数条件下的平面叶栅吹风试验 ,测取了型面压力分布、出口气流角以及叶栅损失等重要气动特性参数。试验研究表明氧涡轮的喷嘴叶栅的设计是成功的 ,具有良好的气动特性 ,可以有效地应用于液体火箭发动机的涡轮中。本文研究也为该类喷嘴叶栅的设计提供了有用的实验数据和指导意义的结论
A nozzle cascade for a turbocharged turbojet engine with high thrust was designed to investigate the aerodynamic characteristics of the nozzle cascade and verify the aerodynamic design of the nozzle cascade. The multi-speed nozzle cascade using advanced post-load flow control technology to reduce the cascade secondary flow loss. Four inlet airflow angles and three outlet isal entropy Mach number blowing tests were carried out on the nozzle cascade. The important aerodynamic parameters such as pressure distribution at the surface, outlet flow angle and cascade loss were measured. Experimental studies have shown that the design of the nozzle cascade of oxygen turbine is successful and has good aerodynamic characteristics, which can be effectively applied to the turbine of a liquid rocket engine. This study also provides useful experimental data and guiding conclusions for the design of nozzle cascades