吸力面翼刀对压气机叶栅内二次流的影响  

Effect of using blade boundary layer fences on the secondary flow in compressor cascade

作　　者：刘艳明[1] 钟兢军[2] 伍耐明[1] 董金钟[1] 周盛[1] 

机构地区：[1]北京航空航天大学能源与动力工程学院,北京100083 [2]大连海事大学机电与材料工程学院,辽宁大连116026

出　　处：《推进技术》2006年第4期316-320,共5页Journal of Propulsion Technology

基　　金：国家自然科学基金资助项目(50076009)

摘　　要：对CDA常规直叶栅和具有不同展向位置和高度的吸力面翼刀压气机叶栅内三维粘性流场进行了数值模拟。结果表明,加装位置越高、高度越大的吸力面翼刀对吸力面附近展向流动阻断能力越强;反向翼刀涡的产生与流道内展向流动的强弱息息相关;具有距端壁一个附面层且高度为一个吸力面附面层厚度的翼刀方案为最佳翼刀方案。The numerical simulation was carried out to investigate the effect of the blade fence with different height and different spanwise location on the secondary flow in compressor cascade composed of conventional straight blades. The results show that higher fence will block the spanwise flow better; the counter-rotating fence vortex formation has a close relation with the intensity of spanwise flow. The height of optimal fence,which is located one endwall boundary layer thickness away from the endwall, is equal to the inlet blade boundary layer thickness.

关 键 词：压气机叶栅 吸力面翼刀 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]