Investigation into the Effect of Leading-Edge Contouring on Aero-Thermal Performance in Blade Endwall Region

doi:10.7652/xjtuxb202201015

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Investigation into the Effect of Leading-Edge Contouring on Aero-Thermal Performance in Blade Endwall Region

更新时间：2025-05-08

- Investigation into the Effect of Leading-Edge Contouring on Aero-Thermal Performance in Blade Endwall Region
- Vol. 56, Issue 1, Pages: 130-141(2022)
- 作者机构：
  
  西安交通大学能源与动力工程学院,西安,710049
- 作者简介：
- 基金信息：
- DOI：10.7652/xjtuxb202201015
  CLC： TK47
- Online First：10 January 2022，
  
  Published：2022
- 稿件说明：
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Investigation into the Effect of Leading-Edge Contouring on Aero-Thermal Performance in Blade Endwall Region[J]. 2022, 56(1): 130-141.
DOI：

Investigation into the Effect of Leading-Edge Contouring on Aero-Thermal Performance in Blade Endwall Region[J]. 2022, 56(1): 130-141. DOI： 10.7652/xjtuxb202201015.

摘要

采用数值计算方法研究了前缘倒角造型动叶的端区气热性能

分析了3种前缘形式(无倒角、直线型倒角、抛物线型倒角)的叶片端区的二次流结构、气动损失和传热特性

对比了有、无前缘倒角时马蹄涡和通道涡对端区流动传热性能的影响机制。结果表明:前缘倒角造型显著减小了端壁前缘区域的切应力、通道下游偏转角和前缘倒角角区的马蹄涡尺寸和强度

但对通道涡的抑制作用较小; 前缘倒角削弱了端区横向二次流动

使得通道下游总压损失减小; 抛物线型前缘倒角的角区湍动能和马蹄涡尺寸略小于直线型前缘倒角造型的相应参数; 3种前缘倒角造型叶片通道下游端壁的平均Nu沿流向均逐渐增大; 相对于无前缘倒角造型叶片

带前缘倒角造型叶片的端壁前缘区域节距方向平均Nu最高下降了约40%。

但通道下游端壁节距方向平均Nu仅下降约8%; 在通道下游

抛物线型前缘倒角叶片端壁节距方向平均Nu略低于直线型前缘倒角叶片。

Abstract

The aero-thermal performance in a rotor blade endwall region with leading-edge contouring was numerically investigated with the computational fluid dynamics method. The secondary flow structures

aerodynamic loss and heat transfer characteristics near the endwall were analyzed with three structures of leading-edge fillet contouring

i.e. no leading-edge fillet

linear profiling fillet

and parabolic profiling fillet. The roles of horse-shoe and passage vortices in the flow and heat transfer performance were compared between the cases with and without fillet. The results show that the leading-edge fillet contouring is able to reduce the wall shear stress and yaw angle

and reduce scale and intensity of horse-shoe vortices near the leading edge

but it has a slight suppression effect on the development of passage vortex downstream of the leading edge. Moreover

the leading-edge fillet tends to reduce the transverse flow in the endwall region

resulting in a decreased total pressure loss in the rear part of blade passage. For the parabolic profiling fillet case

the turbulence kinetic energy and horse-shoe vortex scale in the corner area of leading edge are slightly smaller than those of linear profiling fillet case. For all fillet contouring cases

the pitch-averaged Nusselt number downstream of the leading edge is decreased along the streamwise direction. Compared with no leading-edge fillet case

the maximum decrease of pitch-averaged Nusselt number on blade endwall near leading edge reaches about 40%

but it is only reduced by 8% at the rear part of blade passage. At the rear part of blade passage

the pitch-averaged Nusselt number on blade endwall for the parabolic profiling fillet case is slightly lower than that of linear profiling fillet case.

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references

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