Investigation on Film Cooling and Aerodynamic Performance of the Multi-Cavity Tip with Inclined Film Holes in a Linear Turbine Cascade

JIA Zhe; LI Feng; ZHANG Weixin; LIU Zhao; SHI Yan; FENG Zhenping

doi:10.7652/xjtuxb202309002

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Investigation on Film Cooling and Aerodynamic Performance of the Multi-Cavity Tip with Inclined Film Holes in a Linear Turbine Cascade

更新时间：2025-07-09

- Investigation on Film Cooling and Aerodynamic Performance of the Multi-Cavity Tip with Inclined Film Holes in a Linear Turbine Cascade
- Vol. 57, Issue 9, Pages: 10-21(2023)
- 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/xjtuxb202309002
  CLC： V231.1
- Online First：10 September 2023，
  
  Published：2023
- 稿件说明：
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JIA Zhe, LI Feng, ZHANG Weixin, et al. Investigation on Film Cooling and Aerodynamic Performance of the Multi-Cavity Tip with Inclined Film Holes in a Linear Turbine Cascade[J]. 2023, 57(9): 10-21.
DOI：

JIA Zhe, LI Feng, ZHANG Weixin, et al. Investigation on Film Cooling and Aerodynamic Performance of the Multi-Cavity Tip with Inclined Film Holes in a Linear Turbine Cascade[J]. 2023, 57(9): 10-21. DOI： 10.7652/xjtuxb202309002.

摘要

为提高燃气透平动叶叶顶的气膜冷却有效度

并减少由叶顶泄漏流引起的气动损失

对带倾斜圆柱孔的多凹槽叶顶冷却与气动特性进行了研究

试验测量了多凹槽叶顶的气膜冷却特性

并对其气动特性进行了数值模拟分析。首先采用压力敏感漆技术

在4种吹风比(0.5、1.0、1.5和2.0)下

测量了4种多凹槽叶顶(凹槽数分别为1、2、3和4个)气膜冷却性能的变化规律; 然后经湍流模型验证

采用与试验数据吻合最好的SST k-ω模型

分析了多凹槽叶顶的流场结构及气动损失。研究结果表明:多凹槽叶顶在叶顶区域前、中部具有更优良的气膜冷却有效度

同时对肩壁也有良好保护作用; 由于多凹槽叶顶的肋能够阻挡冷气向下游流动

肋后能形成涡卷吸冷气

因而能够提高肋前和肋后的气膜冷却有效度; 相较于单凹槽叶顶

多凹槽叶顶的气动损失较低

其中三凹槽叶顶的总压损失系数最小

最多比单凹槽叶顶的低9.3%。

Abstract

In order to improve the film cooling effectiveness and reduce the aerodynamic loss of the gas turbine blade tips

an experiment was conducted to investigate the film cooling characteristics of the multi-cavity tips with inclined film holes

and the aerodynamic performance of these tips was numerically simulated. Firstly

the variation rule of the film cooling performance of four types of multi-cavity tips

of which the cavity number was one

two

three and four respectively

was measured under four blowing ratios(0.5

1.0

1.5 and 2.0)by the pressure sensitive paint technique. Secondly

after the validation of turbulence models

the SST k-ω turbulence model

which showed the most excellent agreement with experimental results

was adopted to simulate the flow field structure and aerodynamic loss of the multi-cavity tips. The results show that the multi-cavity tips have better film cooling coverage on the front and middle parts of the tips as well as the rims; the installed ribs of the multi-cavity tips can prevent the coolant from flowing downstream and induce vortices behind the ribs to involve the coolant

leading to better film cooling effectiveness on the upstream and downstream parts of the ribs; compared with the conventional cavity tips

the aerodynamic loss of the multi-cavity tips are lower

of which the three-cavity tips performs the lowest loss coefficient and it is 9.3% lower than that of the conventional cavity tip at most.

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