高负荷跨音速压气机转子气动设计及附面层抽吸研究

Aerodynamic Design of a High Load Transonic Compressor's Rotor and Primarily Research of the Flow Details in the Transonic Blades by Boundary Layer Suction

本文设计了一跨音速压气机转子,其叶尖切线速度420 m/s,在确保动叶出口参数的同时,压比达到3.2,绝热等熵效率88.7%。数值模拟表明,60%叶高到叶顶区域,气体分离严重。为了有效控制分离,本文初步探讨了抽吸附面层对转子性能的影响。结果表明抽气能明显影响附面层的发展与激波的空间结构,转子局部性能得到改善。

This text has designed a transonic compressor＇ s rotor with 420 m/s tangential velocity speed and attained pressure ratio as 3.2, adiabatic isentropic efficiency as 88.7%. In order to control the seri- ously boundary layer separation from the 60% high of the blade to the tip region, this paper has re- searched the flow detgils by boundary layer suction primarily. And the results show that the suction can influence the boundary layer development and the structure of the shock obviously. Part of the flow in the rotor is optimized but not helpful to increase the whole performance of the rotor.