摘要
对可控扩散叶型(CDA)常规直叶栅和三种具有不同长度和流向位置的端壁翼刀叶栅内的三维粘性流场进行了数值模拟。结果表明,不同长度端壁翼刀都不同程度上改善了栅内的气流流动状况;较小长度的翼刀所产生的附加损失也较小;反向翼刀涡的产生与流道内横向流动的强弱息息相关。计算结果表明,占据前3/4流道长的翼刀为最佳翼刀。
The numerical simulation has been carried out to investigate the influence of the endwall wing fence with different length on the secondary flow in compressor cascade.The results show that the boundary layer fences can reduce the strong cross-flow in cascade near the endwall.The additional energy loss of long-fence is larger than that of short-fence.A counter-rotating streamwise vortex was found over the fence and the strength is closely related to the strength of the crossflow.The numerical results show that the influence on secondary flow is most effective when the fences are located in the foreside of the passage with a length of 75 percent axial chord.
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
2004年第5期666-670,共5页
Journal of Aerospace Power
基金
国家自然科学基金资助项目(50076009)
973项目
全国优秀博士学位论文作者专项基金资助项目(199932)
关键词
叶栅
翼刀
二次流
能量损失
航空航天
推进系统
aerospace propulsion system
compressor cascade
wing fence
secondary flow
additional energy loss
