Experimental investigation of film cooling efficiency on turbine blade surface with one-inlet and double-outlet hole injection

ZHANG Wei; WU Chaolin; LI Guangchao; KOU Zhihai

English

您当前的位置：

首页 >

文章列表页 >

Experimental investigation of film cooling efficiency on turbine blade surface with one-inlet and double-outlet hole injection

Thermal Power Generation Vol. 44, Issue 5, Pages: 17-21(2015)

更新时间：2025-09-28

- Experimental investigation of film cooling efficiency on turbine blade surface with one-inlet and double-outlet hole injection
- 作者机构：
  
  1. 沈阳航空航天大学辽宁省航空推进系统先进测试技术重点实验室
  2. 中国航空工业集团公司中国燃气涡轮研究院
- 作者简介：
- 基金信息：
- DOI：
  CLC： TK471
- Published：2015
- 稿件说明：
移动端阅览
ZHANG Wei, WU Chaolin, LI Guangchao, et al. Experimental investigation of film cooling efficiency on turbine blade surface with one-inlet and double-outlet hole injection[J]. Thermal Power Generation, 2015, 44(5): 17-21.
DOI：

ZHANG Wei, WU Chaolin, LI Guangchao, et al. Experimental investigation of film cooling efficiency on turbine blade surface with one-inlet and double-outlet hole injection[J]. Thermal Power Generation, 2015, 44(5): 17-21. DOI：

摘要

将单入口-双出口孔分别布置在叶片型面压力面和吸力面进行试验

研究了吹风比分别为1.0

1.5和2.0时

气膜孔下游气膜冷却特性。结果表明:吸力面吹风比为1.5时冷却效率最大

吹风比为1.0时冷却效率最小

沿流向冷却效率降幅随吹风比增加而减小;压力面冷却效率分布较为复杂

气膜孔出口附近吹风比为1.0时冷却效率最高

下游较远处吹风比为2.0时冷却效率最大

吹风比为1.0时冷却效率最小

沿流向不同吹风比下的冷却效率变化规律不同。

Abstract

An experimental investigation was conducted to obtain the detailed film cooling efficiency distributions on both pressure side and suction side of turbine blade with a novel film hole injection.The blowing ratios of the coolant through the discrete holes are 0.5

1.0and 2.0

respectively.Detailed film cooling efficiency distributions and spatially averaged film cooling efficiency were obtained.The results show that the film cooling efficiency at the pressure side and the suction side was different.The suction side had the highest cooling efficiency at blowing ratio of 1.5.The increasing blowing ratio led to a much faster decrease in the spanwise averaged efficiency.The cooling efficiency distribution of the pressure side was complicated.The cooling efficiency at the hole exit reached the highest at blowing ratio of 1.0

while that at the down stream reached the highest at blowing ratio of 2.0and the lowest at 1.0.The efficiency distributions were different with the various blowing ratios.

关键词

Keywords

references

Views

161

下载量

CSCD

Alert me when the article has been cited

提交

Publicity Resources

Influence of coolant crossflow on film cooling effectiveness of one-inlet and double-outlet injection holes

Influence of temperature ratio on cooling efficiency of 3-in-1 hole injection film

Numerical simulation on cooling effectiveness of gas film on tip of blade with groove and fins

Investigation on film cooling effectiveness of fanned hole with broad outlet

Related Author

ZHANG Guochen

LI Guangchao

PENG Ningjian

ZHANG Wei

KOU Zhihai

MAO Xiaodong

ZHANG Wei

LI Guangchao

Related Institution

Liaoning Key Lab of Advanced Measurement and Test Technique for Aviation Propulsion System, Faculty of Aerospace Engineering, Shenyang Aerospace University

Aeroengine and Energy Engineering College,Shenyang Aerospace University

China Aviation Industry Corporation Shenyang Engine Design and Research Institute

Liaoning Key Lab of Advanced Measurement and Test Technology for Aviation Propulsion System,Faculty of Aerospace Engineering,Shenyang Aerospace University Shenyang

Liaoning Key Lab of Advanced Test and Measurement for Aviation Propulsion System,Shenyang Aerospace University

AI问答

⁰