傅里叶函数前缘仿生压气机叶栅性能研究  

Investigation on Bionic Compressor Cascade Performance With Fourier Function Leading Edge

作　　者：李润泽 李赫飞 姜斌[1] 郑群[1] 何宏伟[2] LI Run-Ze;LI He-Fei;JIANG Bin;ZHENG Qun;HE Hong-Wei(School of Power and Energy,Harbin Engineering University,Harbin 150001,China;AVIC Aerodynamics Research Institute,Harbin 150001,China)

机构地区：[1]哈尔滨工程大学动力与能源工程学院,哈尔滨150001 [2]中国航空工业空气动力研究院,哈尔滨150001

出　　处：《工程热物理学报》2020年第12期2936-2941,共6页Journal of Engineering Thermophysics

基　　金：国家自然科学基金资助项目(No.51676050);国家科技重大专项(No.2017-Ⅱ-0006-0019,No.2017-Ⅰ-0009-0010);航空科学基金资助项目(No.20173227001)。

摘　　要：本文针对仿鲸鳍前缘造型在压气机叶栅中的应用,提出了一种基于傅里叶级数形式的复合函数前缘造型方法。采用数值模拟方法,重点分析了零攻角下仿鲸鳍叶栅流场结构的变化,给出了不同仿鲸鳍前缘在叶栅端区以及叶中部损失抑制的原因和前缘型线特征,优化出一种具有展向非均匀鳍型前缘的仿生叶栅,对非均匀鳍叶栅的性能进行了验证。研究结果表明,仿鲸鳍叶栅在前缘凹陷处形成流向涡对,在凸起处收缩流动形成高能气团,上述流场结构交替出现,抑制了角区及叶中部的分离流动,降低了叶栅的总压损失。基于高阶傅里叶函数的非均匀鳍型能更好地适应叶栅的变攻角特性,非均匀鳍叶栅总压损失系数相比原始叶栅降低了11.45%。Aiming at the application of whale fin bionic leading edge modeling in compressor cascades,this paper proposes a composite function leading edge modeling method based on Fourier series.The numerical simulation method is used to analyze the flow field structure changes of the whale fin bionic cascade at zero angle of attack,and the reasons for the suppression of the loss of the whale fin bionic leading edge in the cascade endwall and the middle of the blade and the characteristics of the leading edge profile are given.A bionic cascade with a non-uniform fin-shaped leading edge was optimized to verify the performance of the non-uniform fin cascade.The results show that the whale fin bionic cascade inhibits the cascade loss by alternately generating high-energy air masses at the raised areas of the leading edge surface and the flow direction vortices pairs in the recessed areas,In which case the separation of the corner area and the separation of the suction surface in the middle of the leaf extension have a restraining effect and reduce the cascade loss.The non-uniform fin type based on the high-order Fourier function can better adapt to the variable attack angle characteristics of the cascade.The total pressure loss coefficient of the non-uniform fin cascade is reduced by 11.45% compared with the original cascade.

关 键 词：压气机叶栅 仿鲸鳍前缘造型 气动性能 

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]