周向槽抽吸影响扩压叶栅流动损失与旋涡结构研究  

Study on Flow Loss and Vortex Structure of Compressor Cascade With Circumferential Suction Groove

作　　者：陆华伟[1] 郑雨晨 郭爽[2] 杨益[1] 张海鑫 钟兢军[1] LU Hua-Wei;ZHENG Yu-Chen;GUO Shuang;YANG Yi;ZHANG Hai-Xin;ZHONG Jing-Jun(Marine Engineering College,Dalian Maritime University,Dalian 116026,China;School of Aeronautics and Astronautics,Dalian University of Technology,Dalian 116024,China)

机构地区：[1]大连海事大学轮机工程学院,大连116026 [2]大连理工大学航空航天学院,大连116024

出　　处：《工程热物理学报》2019年第1期60-67,共8页Journal of Engineering Thermophysics

基　　金：国家自然科学基金资助项目(No.51506022;No.51676023;No.51436002);辽宁省自然科学基金项目(No.201602078);中央高校基本科研业务费专项资金(No.3132018203;No.DUT16K08)

摘　　要：本文以高负荷扩压叶栅为研究对象,探究了周向槽附面层抽吸对叶栅流动损失及旋涡结构的影响,并给出叶栅拓扑结构和旋涡模型。为研究不同抽吸位置及抽吸流量对叶栅损失的影响,分别在前缘前16.6%弦长、前缘、前缘后16.6%弦长以及前缘后33.3%弦长处开设抽吸槽,抽吸流量分别为0.5%和1%。结果表明:附面层抽吸有效降低叶栅流动损失,提高附面层动能,避免低能流体过早分离,小抽吸流量下,附面层动能的提高不足以抵抗槽后低能流体回流所带来的损失.原型叶栅流道内主要存在马蹄涡、通道涡、壁面涡、壁角涡和集中脱落涡五种旋涡结构,附面层抽吸能够削弱通道涡及集中脱落涡强度,改善流动状况。Taking the highly loaded compressor cascade as the research object,this paper explores the influence of circumferential groove boundary layer suction on cascade flow loss and vortex structure, and gives the cascade topology structure and vortex model.In order to study the effect of different suction positions the cascade loss,respectively on the 16.6% chord ahead of the leading edge,the leading edge,leading edge after 16.6% chord and 33% chord opening suctionslot,suction flow rate are 0.5% and 1%.The results show that the boundary layer suction can effectively reduce the flow loss of the cascade,improve the kinetic energy of the boundary layer,and delay the premature separation of the low-energy fluid.Under the small suction flow rate,the kinetic energy of the boundary layer is not raised enough to resist the loss of the backward flow of low energy fluid downstream the suction slot.There are mainly five kinds of vortex structures in the prototype cascade:horseshoe vortex, passage vortex,wall vortex,corner vortex and concentrated shedding vortex.Boundary layer suction can weaken the intensity of passage vortex and concentrated shedding vortex,and improve the flow condition.

关 键 词：高负荷扩压叶栅 附面层抽吸 流动损失 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]