不同参数端壁翼刀对跨音速压气机环形叶栅二次流影响的数值研究  

Numerical investigation of the secondary flow control in a transonic annual compressor cascade using different parameter endwall fences

作　　者：杨凌[1] 钟兢军[1] 韩少冰[1] 

机构地区：[1]大连海事大学轮机工程学院,辽宁大连116026

出　　处：《大连海事大学学报》2011年第4期30-34,共5页Journal of Dalian Maritime University

基　　金：国家自然科学基金资助项目(50076009;50746041)

摘　　要：对采用可控扩散叶型的压气机环形叶栅在跨音速条件下加装7种周向位置、3种高度和3种厚度的端壁翼刀的叶栅流场进行数值模拟.结果表明:能量损失系数随翼刀向吸力面靠近先减小后增加,随翼刀高度和厚度的增加而增加;各翼刀方案叶展中部气流的流动状况较原型叶栅明显改善,但端壁附近的能量损失增加;与通道涡同向的翼刀涡先增强、后减弱、再向反向加强,抑制了通道涡P2的形成和发展.最佳翼刀方案使叶栅能量损失较原型叶栅降低0.45%.The numerical simulation was carried out to investigate the effect of endwall fences with seven kinds of circumferential position,three kinds of height and three kinds of thickness on the secondary flow in a controlled diffusion airfoils（CDA） transonic compressor cascade.Results show that the energy loss reduces firstly and then increases with endwall fence closing to suction surfaces.The higher the fence,the larger the energy loss,and the same as that of the thickness.The flow condition near the middle of blade height with fence is better than that without fence obviously,but the energy loss near endwall increases.The fence vortex intensity increases firstly,then reduces,and then increases toward reverse,which restrains the development of passage vortex P2.Total energy loss of the optimal fence reduces 0.45% comparing with the original cascade.

关 键 词：端壁翼刀 压气机叶栅 跨音速 二次流 能量损失 

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]