前缘形状对可控扩散叶型性能影响

推进技术 ›› 2013, Vol. 34 ›› Issue (7): 890-897.

前缘形状对可控扩散叶型性能影响

刘宝杰,袁春香,于贤君

北京航空航天大学能源与动力工程学院/航空发动机气动热力国防科技重点实验室,北京100191;北京航空航天大学能源与动力工程学院/航空发动机气动热力国防科技重点实验室,北京100191;北京航空航天大学能源与动力工程学院/航空发动机气动热力国防科技重点实验室,北京100191

发布日期:2021-08-15
作者简介:刘宝杰(1971—),男,博士,教授,研究领域为叶轮机气动力学。E-mail:liubj@buaa.edu.cn
基金资助:
国家自然科学基金(51136003；51006007；50976009)。

Effects of Leading-Edge Geometry on Aerodynamic Performance in Controlled Diffusion Airfoil

National Key Laboratory of Science and Technology on Aero-Engine/School of Energy and Power Engineering, Beijing University of Aeronautics and Astronautics, Beijing 100191, China;National Key Laboratory of Science and Technology on Aero-Engine/School of Energy and Power Engineering, Beijing University of Aeronautics and Astronautics, Beijing 100191, China;National Key Laboratory of Science and Technology on Aero-Engine/School of Energy and Power Engineering, Beijing University of Aeronautics and Astronautics, Beijing 100191, China

Published:2021-08-15

摘要/Abstract

摘要： 采用改进的形状函数变换技术(CST)造型方法对一个可控扩散叶型(CDA)的前缘进行优化设计,实现了叶片前缘与叶身连接之间的曲率连续,消除了设计状态下叶片前缘速度尖峰,使得叶片的气动性能得到了显著改善。利用不同的形状函数生成不同的曲率连续前缘,叶型的最小损失相同,可用攻角范围的差别却很大。研究表明,这是由于前缘速度尖峰在非设计工况下的发展变化过程不同造成的。过强的前缘尖峰会导致附面层迅速增厚甚至提前转捩。 

关键词: CST造型方法;可控扩散叶型(CDA);前缘形状;可用攻角范围 

Abstract: Class function/shape function transformation technique(CST) was improved and used to design the leading edge of the controlled diffusion airfoils. This method removes the leading edge curvature discontinuities, eliminates the leading-edge spikes under the design states, and then improves the aerodynamic performance significantly. Different leading-edge shapes with no curvature discontinuities were achieved using different shape function. Although they have the same minimum loss, the available incidence range is quite different. Studies show that it is caused by the different development process of the leading edge spikes under the off-design conditions. Too large spikes could thicken the early suction surface boundary layer rapidly or even cause premature transition.

Key words: CST methodology;Controlled diffusion airfoil;Leading-edge geometry;Available incidence range

刘宝杰,袁春香,于贤君. 前缘形状对可控扩散叶型性能影响[J]. 推进技术, 2013, 34(7): 890-897.

LIU Bao-jie, YUAN Chun-xiang, YU Xian-jun. Effects of Leading-Edge Geometry on Aerodynamic Performance in Controlled Diffusion Airfoil[J]. Journal of Propulsion Technology, 2013, 34(7): 890-897.

参考文献

[1] 陈懋章,刘宝杰.风扇/压气机气动设计技术发展趋势——用于大型客机的大涵道比涡扇发动机 [J].航空动力学报, 2008,3(6).
[2] 钟兢军,王会社,王仲奇.多级压气机中可控扩散叶型研究的进展与展望第一部分可控扩散叶型的设计与发展 [J].航空动力学报, 2001,6(3).
[3] Suder K L,Chima R V,Strazisar A J.The Effect of Adding Roughness and Thickness to a Transonic Axial Compressor Rotor [R].ASME GT-1994-339.
[4] Martin N Goodhand, Robert J.Miller.The Impact of Real Geometries on Three-Dimensional Separations in Compressors [R].ASME GT-2010-22246.
[5] Martin N Goodhand, Robert J Miller.Compressor Leading Edge Spikes:A New Performance Criterion [R].ASME GT 2009-59205.
[6] 刘火星,蒋浩康,陈懋章.压气机叶片前缘分离流动 [J].工程热物理学报.2004,5(6).
[7] Walraevens R E,Cumpsty N A.Leading Edge Separation Bubbles on Turbomachine Blades [R].ASME-GT-1993-91.
[8] 陆宏志,徐力平,方韧.压气机叶片前缘形状的改进设计 [J].航空动力学报,2000,5(2).
[9] 陆宏志,徐力平.压气机叶片的带平台圆弧形前缘 [J].推进技术.2003,4(6).(LU Hong-zhi, XU Li-ping.Circular Leading Edge with a Flat for Compressor Blades [J].Journal of Propulsion Technology,2003,4(6).)
[10] 陆宏志.叶轮机叶片前缘流动和前缘形状优化 [D].北京:北京航空航天大学,2003.
[11] Brenda M Kulfan,John E Bussoletti.“Fundamental” Parametric Geometry Representations for Aircraft Component Shapes [R].AIAA 2006-6948.
[12] Brenda M Kulfan.A Universal Parametric Geometry Representation Method-“CST” [R].AIAA 2007-0062.
[13] Brenda M Kulfan.“CST” Universal Parametric Geometry Representation Method With Applications to Supersonic Aircraft [C].USA:Fourth International Conference on Flow Dynamics,2007.