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

LI Guangchao; ZHANG Zhandong; ZHANG Wei; KOU Zhihai; ZHAO Guochang

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

Thermal Power Generation Vol. 45, Issue 10, Pages: 23-28(2016)

更新时间：2025-09-28

- Numerical simulation on cooling effectiveness of gas film on tip of blade with groove and fins
- 作者机构：
  
  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
- 作者简介：
- 基金信息：
- DOI：
  CLC： TK471
- Published：2016
- 稿件说明：
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LI Guangchao, ZHANG Zhandong, ZHANG Wei, et al. Numerical simulation on cooling effectiveness of gas film on tip of blade with groove and fins[J]. Thermal Power Generation, 2016, 45(10): 23-28.
DOI：

LI Guangchao, ZHANG Zhandong, ZHANG Wei, et al. Numerical simulation on cooling effectiveness of gas film on tip of blade with groove and fins[J]. Thermal Power Generation, 2016, 45(10): 23-28. DOI：

摘要

为了提高凹槽叶顶的气膜冷却效率

提出了一种凹槽带肋叶顶结构。通过数值模拟方法

研究了叶顶结构在不同吹风比、滑移壁面条件下冷却气体在凹槽腔内的流动状态和气膜冷却效率分布

揭示了凹槽带肋叶顶改善叶顶气膜冷却效率机理。结果表明:吹风比为0.5时

气膜孔附近冷却效率最高;吹风比为1.5时

凹槽内吸力面附近冷却效率最高;肋片导流作用使冷气更大范围地覆盖在凹槽内

提高了平均冷却效率

这种效应在吹风比为0.5时更明显。

Abstract

To enhance the cooling effectiveness of gas film on top of groove blade

a structure of groove blade with fins was proposed.The flow status and gas film cooling effectiveness distribution of cooling gas inside the groove were numerically simulated

under conditions with different blowing ratios and end wall slippage situations.The cooling effectiveness enhancement mechanism of the fins structure was revealed.The results show that

the highest cooling effectiveness appears near the film hole and the suction side at blowing ratio of 0.5and 1.5

respectively.The flow guidance effect the fins improves the film coverage

resulting in an increase in the average film cooling effectiveness on the squealer tip

especially at blowing ratio of 0.5.

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