子午收缩导向叶栅气动性能的实验研究  

Experimental investigation on aerodynamic performance of nozzle blade cascade by meridian shrinked

作　　者：冯子明[1] 韩万金[1] 钟兢军[2] 

机构地区：[1]哈尔滨工业大学能源科学与工程学院,哈尔滨150001 [2]大连海事大学机电与材料工程学院,辽宁大连116026

出　　处：《实验流体力学》2008年第1期65-70,共6页Journal of Experiments in Fluid Mechanics

摘　　要：在环形叶栅低速风洞中,对调节级导向叶栅进行了吹风实验。采用五孔球头测针测量了由栅前至栅后7个横截面内气流参数沿叶高和节距的分布;籍助沿叶型的静压测孔测量了在7个相对叶高位置沿叶型的静压系数;并应用墨迹显示技术,显示了沿上下端壁及叶片表面的极限流线谱。试验结果表明,具有后部加载和较大前缘半径的调节级导向叶栅通过子午收缩获得了良好的气动性能。Adjust stage blade was tested in a low speed annular cascade tunnel. The flow field was measured with five-hole probe, and the measurement sections were located in front of and behind the cascade. The static pressure distributions on the blade surface were measured at 7 sections along the blade height. The ink trace visualization on blade surface and two endwalls were also conducted. The experimental results show that the adjust stage blade with aft-loading and big fore-edge radius had good flow characteristics by meridian shrink.

关 键 词：子午收缩 压力测量 导向叶栅 流动显示 气动性能 

分 类 号：TK26[动力工程及工程热物理—动力机械及工程] V211.7[航空宇航科学与技术—航空宇航推进理论与工程]