压气机环形叶栅中应用吸力面翼刀的数值研究  

NUMERICAL INVESTIGATION OF ANNUAL COMPRESSOR CASCADE WITH SUCTION SURFACE FENCES

作　　者：杨凌[1] 钟兢军[1] 严红明[2] 

机构地区：[1]大连海事大学轮机工程学院,辽宁大连116026 [2]哈尔滨工业大学能源科学与工程学院,黑龙江哈尔滨150001

出　　处：《工程热物理学报》2010年第6期938-942,共5页Journal of Engineering Thermophysics

基　　金：国家自然科学基金资助项目(No.50076009;No.50746041)

摘　　要：对CDA环形叶栅和6种不同叶展高度安装吸力面翼刀的叶栅三维黏性流场进行了数值模拟，结果表明：各翼刀方案的叶展中部流动状况均较原型叶栅有一定改善，叶栅能量损失系数随翼刀安装位置沿叶展高度的增加先降低后增加。在计算范围内，翼刀安装在叶展高度为20％叶高的方案可使分离线高度显著降低。翼刀涡的形成、发展和变化受翼刀一端壁间气流流动情况和翼刀安装高度的影响，翼刀涡与通道涡的相互作用因翼刀安装高度而异。The numerical simulation has been carried out to investigate the effect of suction surface fences on the flow fields in an annual CDA（controlled diffusion airfoils） compressor cascade. The results show that the flow near the middle of blade height with fences is better than that without fences; the cascade loss is reduced firstly and then increased along blade height. The position of the separation line in the cascade with at fence 20% blade height is reduced obviously. The fence vortices are related to the flow between fence and endwall, and the suction surface fence＇s height on the blade surface. The interaction between fence vortex and passage vortex is different with the fence location height along blade.

关 键 词：压气机叶栅 吸力面翼刀 二次流 分离线 叶栅损失 

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]