Effect of blowing ratio on film cooling efficiency of trailing edge on turbine blade

LI Guangchao; YU Quanpeng; ZHANG Wei; KOU Zhihai

doi:10.19666/j.rlfd.201712147

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Effect of blowing ratio on film cooling efficiency of trailing edge on turbine blade

更新时间：2025-09-28

- Effect of blowing ratio on film cooling efficiency of trailing edge on turbine blade
- Thermal Power Generation Vol. 47, Issue 10, Pages: 58-65(2018)
- 作者机构：
  
  沈阳航空航天大学航空航天工程学部(院)
- 作者简介：
- 基金信息：
- DOI：10.19666/j.rlfd.201712147
  CLC： TK47
- Published Online：28 September 2018，
  
  Published：2018
- 稿件说明：
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LI Guangchao, YU Quanpeng, ZHANG Wei, et al. Effect of blowing ratio on film cooling efficiency of trailing edge on turbine blade[J]. Thermal power generation, 2018, 47(10): 58-65.
DOI：

LI Guangchao, YU Quanpeng, ZHANG Wei, et al. Effect of blowing ratio on film cooling efficiency of trailing edge on turbine blade[J]. Thermal power generation, 2018, 47(10): 58-65. DOI： 10.19666/j.rlfd.201712147.

摘要

为了探索涡轮叶片尾缘劈缝冷却特性

针对后台阶三维劈缝冷却模型

采用数值模拟方法研究了吹风比Br=0.5、0.8、1.0、1.5时的气膜冷却效率。结果表明:后台阶区域劈缝下游气膜冷却效率比肋下游气膜冷却效率在小吹风比(Br=0.5)时高10.9%～39.1%

在大吹风比(Br=1.5)时高53.5%～56.0%;Br越大

后台阶气膜冷却效率沿流向降低速度越快

后台阶尾部气膜冷却效率沿半圆柱周长方向降低速度越慢;肋下游后台阶尾部

Br为0.8和1.0时气膜冷却效率比Br为0.5和1.5时高7.0%左右;后台阶尾部是气膜冷却的薄弱部位

其面积加权平均气膜冷却效率比后台阶低37.0%～39.0%;Br为0.8、1.0时

后台阶及其尾部的面积加权平均气膜冷却效率最高

较Br=0.5时高9.0%～11.0%

较Br=1.5时高3.0%～6.0%。

Abstract

In order to investigate the cooling characteristics of the trailing edge on turbine blade

numerical simulation method was used to study the film cooling effectiveness at the blowing ratios of 0.5

0.8

1.0 and 1.5 for the three-dimensional split cooling model of the backward-facing step. The results show that

in the backwardfacing step area

the film cooling effectiveness in the downstream of the split slot is 10.9%～39.1% higher than that of the ribs at small blowing ratio of 0.5 and 53.5%～56.0% higher at big blowing ratio of 1.5. The higher the blowing ratio is

the faster the film cooling effectiveness of the backward-facing step decreases along the gas flow direction

and the lower the film cooling effectiveness of the tail of backward-facing step decreases along the direction of the semi-cylindrical circumference. On the downstream of the tail ribs of backward-facing step

the film cooling effectiveness of blowing ratio of 0.8 and 1.0 are about 7.0% higher than that of 0.5 and 1.5. The backward-facing step tail is the weak part of the film cooling

and its area-weighted average film cooling effectiveness is 37.0%～39.0% lower than that of the backward-facing step. When the blowing ratio is 0.8 and 1.0

the area-weighted average film cooling effectiveness of the backward-facing step and its tail is the highest

which is 9.0%～11.0% higher than that of the blowing ratio of 0.5

and 3.0%～6.0% higher than that of the blowing ratio of 1.5.

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