某型轴流压气机高压第16级叶型气动特性的试验研究

Experimental Study on Aerodynamic Characteristics of Profiles in Sixteenth High Pressure Stage of an Axial Compressor

采用环形亚声速风洞气动参数测量试验方法,研究了某型轴流压气机高压第16级动、静叶型的变攻角特性。试验结果表明,对于扩压叶型,沿压力边和吸力边的流动都是先快速膨胀后扩压,扩压占流程的绝大部分,相对压力边,吸力边扩压流程长,梯度大,吸力边是叶型损失源;在相同攻角下,叶型损失正比于叶型的几何折转角,因为在试验攻角变化范围内,叶型的落后角可忽略不计。

The characteristics of the variable attack angle of static blades and moving blade profiles in the sixteenth high-pressure stage of a axial flow compressor are studied by using the test method of aerodynamic parameter measurement on annular subsonic wind tunnel.The test results show that for diffuser blade profiles,the flow along pressure edge and suction edge expands rapidly before diffusing,and diffusing accounts for the majority of the process.Relative pressure edge,suction edge diffusing process is long,gradient is large,suction edge is the source of loss of blade profile.At the same angle of attack,the losses of blade profile are proportional to the geometric turning angle of the blade profiles,because in the range of test angles of attack,the lag angles of the blade profiles can be neglected.