吸力面小翼对扩压叶栅旋涡结构的影响  

The Influence of Vortex Structure With Suction-Side Winglet in Compressor Cascade

作　　者：钟兢军[1] 阚晓旭[1] 陆华伟[1] 韩少冰[1] 甘久亮[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：《工程热物理学报》2014年第1期46-50,共5页Journal of Engineering Thermophysics

基　　金：国家自然科学基金资助项目(No.51076018;No.51206013);高等学校博士学科点专项科研基金(No.20112125120009);中央高校基本科研业务费专项资金

摘　　要：本文采用经过实验校核的数值模拟方法对某压气机动叶原始叶型和吸力面叶尖小翼叶型流道旋涡结构进行了详细分析.结果表明,原始叶栅流道中存在四个旋涡,即上通道涡、下通道涡、下集中脱落涡和叶顶泄漏涡。吸力面叶尖小翼的应用使得叶栅流道内的旋涡结构发生了变化,叶尖小翼抑制了叶顶泄漏涡的强度,从而使得上集中脱落涡得以出现,同时还使得叶顶泄漏涡的衍生涡被撕裂成两个衍生涡.正是由于叶尖小翼改变了叶栅流道内的旋涡结构,使叶栅流场的气动性能得到了改善.Based on the experimental verification, this paper analyzed the passage vortex structures of original blade and suction-side blade tip winglet in detail by using the numerical simulation method. The results show that there are four vortex structures in the original cascade passage, namely the up passage vortex, the down passage vortex, the up shedding vortex and the tip leakage vortex. The application of Suction-side blade tip winglet makes the vortex structure inside the cascade passage changed, blade tip winglet inhibit the tip leakage vortex intensity, in order to make the shedding vortex to appear, and it also makes the tip leakage vortex the deriving into two derivative vortex. It is because of blade tip winglet changed cascade passage inside the vortex structure, improving the cascade flow field of the pneumatic performance.

关 键 词：矩形扩压叶栅 叶尖小翼 叶顶泄漏涡 旋涡结构 

分 类 号：V235.11[航空宇航科学与技术—航空宇航推进理论与工程]