叶表静压孔对平面叶栅性能的影响

Effect of Surface Static Pressure Hole on the Aerodynamic Performance for a Cascade

为研究某压气机叶栅试验过程中静压孔导致栅后损失增大原因,通过试验校核计算流体动力学方法,研究了叶片表面静压孔对叶栅性能的影响。结果表明:叶片表面静压孔影响了近壁面流场形态,静压测量偏差达到2%,气流在静压孔内形成旋涡,随着旋涡强度增大,有旋气流的生成与脱落对流体产生扰动,使得叶片表面阻力增大,附面层增厚,栅后总压损失加大,1.0 mm静压孔导致栅后总压损失平均值增大了30%,相比之下,静压孔对气流角的影响较小。

In order to study the reason of the increase of the loss caused by the static pressure hole in the test of a compressor cascade,computational fluid dynamics verified by experiment were conducted to investigate the effect of surface static pressure hole on the aerodynamic performance for a high subsonic compressor cascade.Results show that the pressure holes change the flow field near the surface and cause the static pressure measurement deviation reach to 2%.The vortex is generated inside the holes.The generation and shedding of swirling flow disturbed the flow with it strength increases that led to the rise of resistance on surface.It cause boundary layer grow and more total pressure loss.The average total pressure loss rise 30%in condition of1.0 mm static pressure hole.In contrast,the pressure hole has little influence on the flow angle.