采用附面层抽吸孔改善高负荷扩压叶栅性能的研究

Investigation of Improving the Aerodynamic Performance in Highly-Loaded Compressor Cascade by Boundary Layer Suction Holes

通过试验和数值模拟的方法,以高负荷大弯角扩压叶栅为对象,研究了附面层抽吸孔对损失的控制作用.试验工作中,采用五孔L型探针测量叶栅出口截面气动参数.试验和数值模拟结果得出相似的结论,结果表明:孔式附面层抽吸可以较大幅度地提高扩压叶栅的气动性能,控制流道内的流动损失;出口截面高损失区域缩小,并向下端壁靠拢,流道中部损失减小明显,但对角区的作用并不显著;增加抽吸量对叶栅气动性能的提高并不明显,大抽吸量时反而增加了局部区域的流动损失.

The detailed experiment and numerical simulation were carried out to analyze the effects of boundary layer suction hole on loss control of highly-loaded large bending angle compressor cascade suction surface. In experiment, the exit aerodynamic parameters were measured by five-hole aerodynamic probe. Experimental and numerical results come to similar conclusions. The results show that boundary layer suction can effectively improve aerodynamic performance of compressor cascade, reduce the loss of flow. High-loss area at the exit section diminishes and get close down to the end-wall. The loss decreases obviously in the region of middle blade, but not in the end-wall region. When using big-hole suction, suction volume increases at the same time may result in loss increase in the region nearly 20% blade-high from the end walls.