“孔窝群”端壁压气机叶栅实验研究  

AN EXPERIMENTAL INVESTIGATION OF PIT-ARRAY-PLATE COMPRESSOR CASCADE

作　　者：张叔农[1] 严明[1] 任丽芸[1] 彭泽琰[1] 

机构地区：[1]北京航空航天大学

出　　处：《航空动力学报》1999年第4期401-404,共4页Journal of Aerospace Power

摘　　要：本文介绍在平面叶栅风洞上进行的“孔窝群”端壁叶栅和原始（光滑）端壁叶栅对比试验研究结果。试验研究结果表明，采用“孔窝群”端壁叶栅可以达到下述作用和效果：阻尼气流横向迁移，延缓通道涡的形成或减弱通道涡的强度，使叶栅端区出口气流角过转减少且沿展向分布更为均匀；可以适度增加叶栅端区掺混，从而降低端区低能堆积，降低大攻角（例如：５°，８°和１２°时）状态下的叶栅损失系数；在攻角５°至１２°范围内，“孔窝群”端壁叶栅流通能力增加明显。An experimental investigation of end wall flow control for pit-array cascade plate in a compressor cascade wind tunnel has been completed.The experimental comparison of pit-array-plate with original cascade plate shows that:(1)The movement of flow along pitchwise could be obstructed.It delays the formulation or reduces the intensity of passage-vortex;(2)The flow mixing around the end wall region of the cascade could be moderately increased.The accumulation of lower-level-energy air in the corner may be reduced.(3)The flux across cascade increases obviously at a higher incidence.It is beneficial to improve compressor characteristic map and engine performance.

关 键 词：端壁 压气机 叶栅 实验研究 航空发动机 

分 类 号：V231.3[航空宇航科学与技术—航空宇航推进理论与工程]