发动机氧涡轮喷嘴叶栅气动特性的试验研究

Experimental Investigation on Aerodynamic Characteristics of Nozzle Cascade for Oxygen Turbine of Engine

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。

An experimental study on aerodynamic characteristics of nozzle cascades for oxygen turbine of large thrust liquid rocket engine was conducted, in order to investigate its aerodynamic behaviors and testify its aerodynamic design. The nozzle cascade was designed for a Curtis stage using an advanced after-loaded flow control technique to reduce secondary flow losses. Plane cascade tests were carried out for the cascade under four inlet flow angles and three outlet isentropic Mach numbers, and the important parameters such as surface pressure on blade, outlet flow angle and cascade losses were measured. The experimental results indicate that the design of nozzle for the oxygen turbine is successful, and the nozzle has good aerodynamic behavior and can be used effectively in the turbine of liquid rocket engines. Furthermore, the present research provides some useful test data and guidelines for the nozzle cascade design of such type.