Experimental and Numerical Investigation on Cooling and Aerodynamic Performance of Turbine Blade Ribbed Squealer Tip

  • LIU Zhao ,
  • JIA Zhe ,
  • XU Yao ,
  • FENG Zhenping
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  • Institute of Turbomachinery, Shaanxi Engineering Laboratory of Turbomachinery and Power Equipment, School of Energy and Power Engineering, Xi’an Jiaotong University, Xi’an 710049, China

网络出版日期: 2025-05-06

基金资助

This work was supported by the National Science and Technology Major Project (J2019-III-0007-0050).

版权

Science Press, Institute of Engineering Thermophysics, CAS and Springer-Verlag GmbH Germany, part of Springer Nature 2025

Experimental and Numerical Investigation on Cooling and Aerodynamic Performance of Turbine Blade Ribbed Squealer Tip

  • LIU Zhao ,
  • JIA Zhe ,
  • XU Yao ,
  • FENG Zhenping
Expand
  • Institute of Turbomachinery, Shaanxi Engineering Laboratory of Turbomachinery and Power Equipment, School of Energy and Power Engineering, Xi’an Jiaotong University, Xi’an 710049, China

Online published: 2025-05-06

Supported by

This work was supported by the National Science and Technology Major Project (J2019-III-0007-0050).

Copyright

Science Press, Institute of Engineering Thermophysics, CAS and Springer-Verlag GmbH Germany, part of Springer Nature 2025

摘要

动叶叶顶是燃气轮机中热负荷最高的部位之一,并且由于动叶叶顶间隙内流场十分复杂,叶顶的冷却十分困难。为发展叶顶结构,研究了肋对凹槽叶顶冷却及气热特性的影响。基于基础凹槽叶顶结构,设计了带有不同数量肋的凹槽叶顶结构(分别记为1R、2R和3R,基础结构记为Basic),并在五种不同的吹风比下,使用压力敏感漆(PSP)技术测量了气膜冷却有效度,并以此来分析不同结构的冷却性能。采用经实验验证的数值方法来辅助分析叶顶间隙内的流场以及整体的气动性能。实验结果表明,随着冷气供应量越来越充足,即吹风比M增大,冷气覆盖范围和气膜冷却有效度均逐渐上升。与Basic结构相比,带肋凹槽叶顶中部的气膜冷却有效度较高而尾部的冷却有效度偏低。流场分析结果显示,在Basic结构中,冷气能够向下游流动,直至叶片尾缘,为尾缘部分带来额外的冷却作用。而在带肋凹槽叶顶结构中,肋片诱导流体在其后方形成涡,卷吸肋附近及上游的冷气,并阻碍上游冷气向下游发展,这导致局部冷却性能得到提升而下游区域的冷却性能下降。从气动性能来看,尽管带肋凹槽叶顶的泄漏流流量大于Basic结构,但其在气动性能上的表现优于Basic结构,压力损失系数的降幅最大达到了16.2%。这表明,虽然带肋凹槽叶顶会增加叶顶泄漏流流量,但它们在整体的气动性能上具有显著优势。

本文引用格式

LIU Zhao , JIA Zhe , XU Yao , FENG Zhenping . Experimental and Numerical Investigation on Cooling and Aerodynamic Performance of Turbine Blade Ribbed Squealer Tip[J]. 热科学学报, 2025 , 34(3) : 819 -833 . DOI: 10.1007/s11630-025-2026-4

Abstract

As one of the hottest components of gas turbine, the blade tip is difficult to be cooled down for the complexity flow field in the tight tip clearance. The blade tip protection requires advanced tip structures. To develop new structures, the effect of ribs on blade squealer tip aerothermal performance and cooling performance were investigated. Ribbed squealers tips (1R, 2R and 3R, compared to the Basic case) were designed and their cooling ability under five coolant blowing ratios (M) were measured by the Pressure Sensitive Paint (PSP) technique, taking film cooling effectiveness (η) as the criterion. Numerical method was validated and then was adopted to analyze the flow field and aerodynamic loss in the tip gap. The results indicated that the cooling coverage and η increase with M for sufficient coolant supply. Compared to the Basic case, the η on the middle section is higher while that on the trailing part is lower for the ribbed squealer tips. The flow field analysis showed that the coolant flows downstream to the trailing edge in the Basic case, bringing additional cooling protect to the downstream region. The ribs induce vortices behind them to involve the local and upstream coolant and prevent upstream coolant from flowing down, leading to the improvement in the local and the degradation in the downstream for the film cooling performance. The aerodynamic results pointed out that the ribbed squealer tips are superior to the Basic case in terms of the aerodynamic performance, even though the tip leakage mass flow of these cases are larger than that of the Basic case. The maximum reduction on pressure loss coefficient is 16.2% for the ribbed squealer tip.

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