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

BAI Tao; ZOU Zheng-ping; ZHANG Wei-hao; ZHOU Kun; LIU Huo-xing

doi:10.13224/j.cnki.jasp.2014.06.031

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

更新时间：2026-07-07

- Mechanism of effect of leading-edge geometry on theturbine blade cascade loss
- Issue 6, (2014)
- 作者机构：
  
  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
- 作者简介：
- 基金信息：
- DOI：10.13224/j.cnki.jasp.2014.06.031
  CLC：
- Published：2014
- 稿件说明：
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白涛, 邹正平, 张伟昊, 周琨, 刘火星. 前缘形状对涡轮叶栅损失影响的机理[J]. 航空动力学报, 2014, (6): 1482-1489. doi: 10.13224/j.cnki.jasp.2014.06.031

BAI Tao, ZOU Zheng-ping, ZHANG Wei-hao, et al. Mechanism of effect of leading-edge geometry on theturbine blade cascade loss[J]. 2014, (6).
白涛, 邹正平, 张伟昊, 周琨, 刘火星. 前缘形状对涡轮叶栅损失影响的机理[J]. 航空动力学报, 2014, (6): 1482-1489. doi: 10.13224/j.cnki.jasp.2014.06.031 DOI：

BAI Tao, ZOU Zheng-ping, ZHANG Wei-hao, et al. Mechanism of effect of leading-edge geometry on theturbine blade cascade loss[J]. 2014, (6). DOI： 10.13224/j.cnki.jasp.2014.06.031.

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.

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.

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Related Institution

Collaborative Innovation Center for Advanced Aero-Engine

Department of Mechanics，School of Mechanical Engineering，Tianjin University

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College of Energy and Power Engineering，Nanjing University of Aeronautics and Astronautics

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