压气机叶片钝头前缘对边界层气动影响

推进技术 ›› 2018, Vol. 39 ›› Issue (2): 299-307.

压气机叶片钝头前缘对边界层气动影响

李乐,刘火星,李鹏

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家级重点实验室，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家级重点实验室，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家级重点实验室，北京 100191

发布日期:2021-08-15
作者简介:李乐，男，博士生，研究领域为低速叶栅气动特性与调节。

Aerodynamic Influence of Compressor Blade with Blunt Leading Edge on Boundary Layer Performance

National Key Laboratory of Science and Technology on Aero-Engine Aero-Thermodynamics，School of Energy and Power Engineering，Beihang University，Beijing 100191，China,National Key Laboratory of Science and Technology on Aero-Engine Aero-Thermodynamics，School of Energy and Power Engineering，Beihang University，Beijing 100191，China and National Key Laboratory of Science and Technology on Aero-Engine Aero-Thermodynamics，School of Energy and Power Engineering，Beihang University，Beijing 100191，China

Published:2021-08-15

摘要/Abstract

摘要： 由于加工误差、外物损伤等原因，压气机叶片前缘容易产生钝头变形。为分析其带来的影响，使用 SST湍流模型并结合γ-θ转捩模型进行了数值模拟。通过叶片吸力面边界层形状因子、法向平均间歇因子和叶栅出口总压损失系数等参量，研究了钝头前缘对边界层发展所带来的影响。同时针对一种前缘曲率连续的改进叶型进行了研究。结果表明在很宽的攻角范围内，压力面边界层受钝头变形影响极小。吸力面边界层受影响程度则会随着攻角增大而提高，当攻角超过一定范围，钝头前缘会显著改变边界层发展，影响整个主流流场。

关键词: 压气机；叶片；前缘；钝头；边界层气动性能

Abstract: Due to various reasons， like machining error and foreign objects damage (FOD)， the leading-edge of the compressor blade is likely to blunting. In order to study the blunting influence， numerical simulation based on SST Model and γ-θ Transition Model is used. The influence of blunt leading-edge on boundary layer is studied by analyzing the boundary layer’s shape factor， normal average intermittency factor， blade cascade’s total pressure loss and other parameters. Besides， an optimized blade shape with continuous leading-edge curve is also analyzed. It is demonstrated that pressure surface boundary layer is hardly influenced by blunt leading-edge within a wide range of incidence angle. Suction surface boundary layer is more seriously affected with incidence angle enlargement. When the incidence angle is beyond the limits， the blunt leading-edge will significantly influence the boundary layer， and even the whole main flow field.

Key words: Compressor；Blade；Leading edge；Blunting；Boundary layer aerodynamic performance

李乐,刘火星,李鹏. 压气机叶片钝头前缘对边界层气动影响[J]. 推进技术, 2018, 39(2): 299-307.

LI Le,LIU Huo-xing,LI Peng. Aerodynamic Influence of Compressor Blade with Blunt Leading Edge on Boundary Layer Performance[J]. Journal of Propulsion Technology, 2018, 39(2): 299-307.

参考文献

[1] Davis M R. Design of Flat Plate Leading Edges to Avoid Flow Separation[J]. AIAA Journal, 1980, 18(5): 598-600.
[2] Hodson H P. Boundary-Layer Transition and Separation Near the Leading Edge of a High-Speed Turbine Blade[J]. Journal of Engineering for Gas Turbines and Power, 1985, 107(1): 127-134.
[3] Walraevens R E, Cumpsty N A. Leading Edge Separation Bubbles on Turbomachine Blades[J]. Journal of Turbomachinery, 1995, 117(1): 115-125.
[4] Wheeler P S, Miller J. The Effect of Leading-Edge Geometry on Wake Interactions in Compressors[R]. ASME GT 2007-27802.
[5] Wheeler P S, Miller J. Compressor Wake/Leading-Edge Interactions at Off Design Incidences[R]. ASME GT 2008-50177.
[6] Goodhand N, Miller J. Compressor Leading Edge Spikes: a New Performance Criterion[R]. ASME GT 2009-59205.
[7] Benner M W, Sjolander S A, Moustapha S H. The Influence of Leading-Edge Geometry on Secondary Losses in a Turbine Cascade at the Design Incidence[J]. Journal of Turbomachinery, 2004, 126(2): 277-287.
[8] Reid L, Urasek D C. Experimental Evaluation of the Effects of a Blunt Leading Edge on the Performance of a Transonic Rotor[J]. Journal of Engineering for Power, 1973, 95(3): 199-204.
[9] Elmstron M E, Millsaps K T, Hobson G V, et al. Impact of Nonuniform Leading Edge Coatings on the Aerodynamic Performance of Compressor Airfoils[J]. Journal of Turbomachinery, 2011, 133(4): 041004-9.
[10] Edwards R, Asghar A, Woodason R, et al. Numerical Investigation of the Influence of Real World Blade Profile Variations on the Aerodynamic Performance of Transonic Nozzle Guide Vanes[J]. Journal of Turbomachinery, 2012, 134(2): 115-125.
[11] 陆宏志. 叶轮机叶片前缘流动与前缘形状优化[D]. 北京:北京航空航天大学, 2003.
[12] 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, 24(6): 532-536. (LU Hong-zhi, XU Li-ping, Circular Leading Edge with a Flat for Compressor Blades[J]. Journal of Propulsion Technology, 2003, 24(6): 532-536.)
[13] 刘火星, 李凌, 蒋浩康, 等. 二维NACA65叶型前缘几何形状对气动性能的影响[J]. 工程热物理学报, 2003, 24(2): 231-233.
[14] 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, 25(6): 937-939.
[15] 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.)
[16] 宋寅, 顾春伟. 叶片前缘形状对压气机气动性能的影响[J]. 工程热物理学报, 2013, 34(6): 1052-1054.
[17] 宋寅, 顾春伟. 曲率连续的压气机叶片前缘设计方法[J]. 推进技术, 2013, 34(11): 1474-1481. (SONG Yin, GU Chun-wei. Continuous Curvature Leading Edge of Compressor Blading[J]. Journal of Propulsion Technology, 2013, 34(11): 1474-1481.)
[18] Horton H P. Laminar Separation in Two and Three-Dimensional Incompressible Flow[D]. London: University of London, 1968.
[19] Hatman A, Wang T. A Prediction Model for Separated-Flow Transition[J]. Journal of Turbomachinery, 1999, 121(3): 594-602.　　　　　　　　　　　　　*　收稿日期:2016-12-01；修订日期:2017-02-23。作者简介:李乐,男,博士生,研究领域为低速叶栅气动特性与调节。E-mail: lile199087@163.com(编辑:梅瑛)