前缘形状对涡轮叶栅损失影响的机理

白涛; 邹正平; 张伟昊; 周琨; 刘火星

doi:10.13224/j.cnki.jasp.2014.06.031

前缘形状对涡轮叶栅损失影响的机理

doi: 10.13224/j.cnki.jasp.2014.06.031

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

基金项目:

高等学校博士学科点专项科研基金（20101102110011）

详细信息

作者简介:
白涛（1988- ），女，陕西榆林人，硕士生，主要从事叶轮机械气动的研究.

中图分类号: V231.3
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- 被引次数: 0
出版历程
- 收稿日期: 2013-03-27
- 刊出日期: 2014-06-28

Mechanism of effect of leading-edge geometry on theturbine blade cascade loss

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

摘要

摘要: 通过改变前缘几何形状来分析其在设计攻角、非设计攻角下前缘附近的流动机理.研究结果表明：在宽工况范围内椭圆型前缘表现出了较优越的性能，不但在设计攻角下能很好抑制吸力峰的强度以避免前缘分离泡的产生，而且在较宽的攻角范围内都能保证前缘附近边界层状态基本不变.当正攻角很大时，不同前缘形状前缘附近都会出现分离泡，且会诱导边界层发生转捩，但椭圆型前缘边界层开始发生转捩的攻角会向大攻角方向移动.在20°攻角下，椭圆型前缘叶型的损失相比基准叶型下降了7%左右.进口湍流度的增加不会改变吸力峰的强度但可以减弱前缘分离泡的强度.
- 涡轮 /
- 前缘形状 /
- 吸力峰 /
- 分离泡 /
- 边界层 /
- 湍流度
Abstract: A research on the flow field around leading-edges of different geometries at design and off design incidence was done. It is found that the elliptical leading-edge exhibits better performance, since the elliptical edge can not only depress the pressure spike to successfully avoid the presence of separation bubble near the leading-edge in wide range of working condition, but also keep the boundary layer almost unchanged small in wide range of incidence. When the positive incidence is large, the separation bubble will emerge at the leading-edge of different shapes, inducing the boundary layer transition, however, the research shows that the elliptical leading-edge will bring about the boundary layer transition at larger incidence. The elliptic leading-edge blade decreased about 7% of profile loss compared to baseline blade profile at the insidence of 20°. The increase of the inlet turbulence intensity could depress but not completely suppress the separation bubble at leading-edge.
- turbine /
- leading-edge geometry /
- pressure spike /
- separation bubble /
- boundary layer /
- turbulence intensity

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参考文献(18)

[1]	邹正平,周琨,王鹏,等.大涵道比涡扇发动机涡轮内部流动机理及气动设计技术研究进展[J].航空制造技术,2012,13(1):49-54. ZOU Zhengping,ZHOU Kun,WANG Peng,et al.Research progress on flow mechanism and aerodynamic design method of high-bypass ratio engine turbine[J].Aeronautical Manufacturing Technology,2012,13(1):49-54.(in Chinese)
[2]	邹正平,叶建,刘火星,等.低压涡轮内部流动及其气动设计研究进展[J].力学进展,2007,37(4):551-562. ZOU Zhengping,YE Jian,LIU Huoxing,et al.Research progress on low pressure turbine internal flows and related aerodynamic design[J].Advances in Mechanics,2007,37(4):551-562.(in Chinese)
[3]	Goodhand M N,Miller R J.The impact of real geometries on three-dimensional separations in compressors.ASME Paper GT2010-22246,2010.
[4]	Garzon V E,Darmofal D L.Impact of geometric variability on axial compressor performance[J].Trans ASME,2003,125(10):692-703.
[5]	张伟昊,邹正平,李维,等.叶型偏差对涡轮性能影响的非定常数值模拟研究[J].航空学报,2010,31(11):2131-2138. ZHANG Weihao,ZOU Zhengping,LI Wei,et al.Unsteady numerical simulation investigation of effect of blade profile deviation on turbine performance[J].Acta Aerodynamic et Astronautica Sinica,2010,31(11):2131-2138.(in Chinese)
[6]	张伟昊,邹正平,刘火星.叶型偏差对整机环境中涡轮性能的影响[J].工程热物理学报,2010,31(11):1831-1834. ZHANG Weihao,ZOU Zhengping,LIU Huoxing,et al.Effect of profile deviation on turbine performance in whole engine environment[J].Journal of Engineering Thermophysics,2010,31(11):1831-1834.(in Chinese)
[7]	李宇,邹正平,刘火星,等.叶片安装角偏差对涡轮通道内热斑迁移的影响[J].工程热物理学报,2009,30(6):945-948. LI Yu,ZOU Zhengping,LIU Huoxing,et al.Influence of blade-stagger departure on the migration of hot streak in turbine passage[J].Journal of Engineering Thermophysics,2009,30(6):945-948.(in Chinese)
[8]	Hodson H P.Boundary layer transition and separation near the leading edge of a high-speed turbine balde[J].Journal of Engineering for Gas Turbines and Power,1985,107(1):127-134.
[9]	Hodson H P,Dominy R G.The off design performance of a low-pressure turbine cascade[J].Journal of Turbomachinery,1987,109(2):201-209.
[10]	Walreavens R E,Cumpsty N A.Leading edge separation bubbles on turbomachine blade[J].Journal of Turbomachinery,1995,117(1):115-125.
[11]	Benner M W,Sjolander.S A.Infulence of leading-edge geometry on profile losses in turbine at off-design incidence:experimental results and an improved correlation[J].Journal of Turbomachinery,1997,119(4):193-200.
[12]	Benner M W,Sjolander S A,Moustapha S H.The influence of leading-edge on secondary losses in a turbine cascade at the design incidence[J].Journal of Turbomachinery,2004,126(2):277-287.
[13]	Hamakhan I A,Korakianitis T.Aerodynamic performance effects of leading-edge geometry in gas-turbine blades[J].Applied Energy,2010,87(5):1591-1601.
[14]	陆宏志.叶轮机叶片前缘流动与前缘形状优化.北京:北京航空航天大学,2003. LU Hongzhi.Flow around the leading edge of turbomachinery blading and improved design for leading edge shapes.Beijing:Beijing University of Aeronautics and Astronautics,2003.(in Chinese)
[15]	刘火星,李凌,蒋浩康等.二维NACA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):232-233. LIU Huoxing,LI Ling,JIANG Haokang,et al.Effect of leading-edge geometry on separation bubbles on a NACA65 compressor blades[J].Journal of Engineering Thermophysics,2003,24(2):232-233.(in Chinese)
[16]	ZHANG Weihao,ZOU Zhengping,YE Jian.Leading-edge redesign of a turbomachinery blade and its effect on aerodynamic performance[J].Applied Energy,2012,93(5):655-667.
[17]	张伟昊.低压涡轮内若干流动机理及气动设计问题研究.北京:北京航空航天大学,2013. ZHANG Weihao.Studies o n flow mechanisms and aerodynamic design of low-pressure turbine.Beijing:Beijing University of Aeronautics and Astronautics,2013.(in Chinese)
[18]	冯涛.叶轮机械内部流动分析与设计若干问题.北京:北京航空航天大学,2006. FENG Tao.Some problems of flow analysis and design in turbomachinery.Beijing:Beijing University of Aeronautics and Astronautics,2013.(in Chinese)