摘要
对常规直叶栅和三种具有不同长度和起始位置的吸力面小翼叶栅内的三维黏性流场进行了数值模拟.结果表明,不同长度吸力面小翼都不同程度上改善了叶栅顶部的气流流动状况;在叶顶吸力面侧加装与其型线等长度的小翼可以较好地削弱泄漏涡的强度,随着叶顶间隙的增大,泄漏流动增强,其作用效果逐渐降低.
The numerical simulation was performed to investigate the influence of the suction-side winglet with different lengthes on the tip leakage flow in compressor cascade.The simulation results show that the suction-side winglets can improve the tip clearance flow condition.It is found that the winglet is most effective to weaken the intensity of the leakage vortices if their length is the same with that of the blade tip.With increasing clearance and stronger intensity leakage flow,the winglet＇s effect is gradually decreased.
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
2011年第3期656-661,共6页
Journal of Aerospace Power
关键词
压气机叶栅
吸力面小翼
叶顶间隙
数值模拟
泄漏流
compressor cascade
suction-side winglet
tip clearance
numerical simulation
leakage flow
