隔板位置对透平级凹槽叶顶传热和冷却性能的影响

叶明亮; 晏鑫; 何坤

doi:10.7652/xjtuxb201805017

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隔板位置对透平级凹槽叶顶传热和冷却性能的影响

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- 隔板位置对透平级凹槽叶顶传热和冷却性能的影响
- Effect of Rib Location on the Heat Transfer and Cooling Characteristics at the Squealer Tip in Turbine Stage
- 西安交通大学学报 2018年52卷第5期页码：116-124
- 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：
  
  : 2017-08-01。作者简介: 叶明亮(1995—),男,硕士生;晏鑫(通信作者),男,副教授。基金项目: 国家自然科学基金资助项目(51306138)
- DOI：10.7652/xjtuxb201805017
  中图分类号： TK474.7
- 网络首发：2018-05-10，
  
  纸质出版：2018
- 稿件说明：
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叶明亮, 晏鑫, 何坤. 隔板位置对透平级凹槽叶顶传热和冷却性能的影响[J]. 西安交通大学学报, 2018,52(5):116-124.

Effect of Rib Location on the Heat Transfer and Cooling Characteristics at the Squealer Tip in Turbine Stage[J]. 2018, 52(5): 116-124.
叶明亮, 晏鑫, 何坤. 隔板位置对透平级凹槽叶顶传热和冷却性能的影响[J]. 西安交通大学学报, 2018,52(5):116-124. DOI： 10.7652/xjtuxb201805017.

Effect of Rib Location on the Heat Transfer and Cooling Characteristics at the Squealer Tip in Turbine Stage[J]. 2018, 52(5): 116-124. DOI： 10.7652/xjtuxb201805017.

摘要

采用数值方法研究了燃气透平第1级动叶带3种双凹槽的叶顶传热与冷却性能

双凹槽叶顶的隔板位于凹槽25%、50%和75%弦长位置且垂直于弦长方向(叶顶结构分别称为rib25

rib50和rib75)

并与常规凹槽叶顶的透平级内效率、叶顶传热系数、叶顶气膜冷却有效度进行了对比。结果表明

在无气膜冷却时

不论是常规凹槽叶顶还是双凹槽叶顶

在凹槽底部前缘均存在高传热系数区域; 相比于常规凹槽叶顶

双凹槽叶顶可以提高透平级的总等熵效率

其中rib50的气动性能最好

总等熵效率可以提高0.43%

但叶顶平均传热系数增大13.7%; 叶顶中弧线位置布置气膜冷却孔后

由于叶片的旋转作用和凹槽隔板的限制

使冷气在凹槽内积累

对凹槽底部形成良好的气膜冷却效果; 相对于传统凹槽叶顶

3种双凹槽叶顶的气膜冷却效率显著提高

其中rib50的气膜冷却有效度最大并且气动性能最好

带rib50叶顶的透平级内等熵效率可以提高0.36%

叶顶平均传热系数减小14.4%

叶顶平均气膜冷却有效度提高31.8%。

Abstract

Numerical methods are adopted to investigate the heat transfer and film cooling characteristics at three squealer tips with double cavities in a gas turbine first stage rotor blade. At the squealer tips

the ribs are located at 25%

50% and 75% of axial chord

respectively

and perpendicular to the chord direction

so they are denoted rib25

rib50 and rib75

respectively. The total-to-total isentropic efficiency in the turbine stage

the heat transfer coefficient and the film cooling effectiveness at the blade tip were calculated and also compared with the conventional squealer tip. The results show that

without film cooling

there exists high heat transfer area on the cavity floor near the leading edge for both conventional squealer tip and double-cavity squealer tip. Compared with the conventional squealer tip

the double-cavity squealer tip can improve the total-to-total isentropic efficiency of the turbine stage. Among four squealer tips(conventional squealer tip

rib25

rib50 and rib75)

the aerodynamic performance in rib50 turbine stage is the best

the total-to-total isentropic efficiency can be improved by 0.43%. However

the area-averaged heat transfer coefficient at the rotor blade tip is increased by 13.7% compared with the conventional squealer tip. When the film cooling holes are arranged at the rotor tip camber line

the film cooling effect on the tip cavities is significantly improved because more coolant is accumulated in the cavities

which can be attributed to the blade rotation and the limitation of the rib to coolant. Compared with the conventional squealer tip

the three kinds of double-cavity squealer tips perform superior film cooling effect at the tips. Among the four squealer tips

rib50 performs the best film cooling effect at the rotor tip and also has the highest aerodynamic performance in the turbine stage. With film cooling

the total-to-total isentropic efficiency in the turbine stage equipped with rib50 tip can be increased by 0.36%

the area-averaged heat transfer coefficient at the tip is reduced by 14.4% and the area-averaged film cooling effectiveness can be improved by 31.8% in contrast to the conventional squealer tip.

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Keywords

references

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