不同长度吸力面小翼对压气机叶栅间隙影响的数值研究  

Influence of suction-side winglet length on tip leakage flow in compressor cascade

作　　者：韩少冰[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,大连116026 [2]哈尔滨工业大学能源科学与工程学院,哈尔滨150001

出　　处：《航空动力学报》2011年第3期656-661,共6页Journal of Aerospace Power

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.

关 键 词：压气机叶栅 吸力面小翼 叶顶间隙 数值模拟 泄漏流 

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]