某大折转角压气机静叶分叉改型设计及其尾迹流场  

Redesign and wake flow field for a compressor high-turning stator with bifurcate blade

作　　者：陈焕龙[1] 李林熹 刘华坪[1] 余孟晗 CHEN Huanlong;LI Linxi;LIU Huaping;YU Menghan(School of Energy Science and Engineering,Harbin Institute of Technology,Harbin 150001,China)

机构地区：[1]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》2018年第6期1381-1392,共12页Journal of Aerospace Power

基　　金：国家自然科学基金(51506036;51306042)

摘　　要：针对高负荷风扇/压气机叶栅流道中由于强逆压力梯度而易于诱发大尺度流动分离的问题,基于增加叶栅稠度以减小叶片通道中压力梯度的思想,结合三维叶片造型技术设计了一种分叉叶片结构,应用数值方法对分叉叶片通道气动性能及叶栅尾迹流场特性进行了预测与分析。研究结果表明:与原型叶片通道相比,在设计冲角(0°)及正冲角条件下,分叉叶片通道出口能量损失降低,气流折转能力增加,栅后尾迹亏损大幅度减少。For large scale flow separation problem caused by strong adverse pressure gradient in high-loaded fan/compressor cascade passage,a bifurcate blade was designed by using the three-dimensional blade geometry building technology according to increased solidity,so as to abate pressure gradient in passage flow,and numerical simulation method was adopted to predict and discuss aerodynamic performance and wake flow field characteristics for the design.The results indicated that,compared with baseline blade passage,the energy loss and wake loss decreased as well as flow turning capability was enhanced at 0°and positive incidence angles for bifurcate blade passage.

关 键 词：扩压叶栅 压力梯度 分叉叶片 尾迹 二次流 

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]