Effects of Squealer Tip on Blade Aerodynamic Performance and Tip Heat Transfer in Gas Turbine

杨佃亮; 丰镇平

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Effects of Squealer Tip on Blade Aerodynamic Performance and Tip Heat Transfer in Gas Turbine

更新时间：2025-12-08

- Effects of Squealer Tip on Blade Aerodynamic Performance and Tip Heat Transfer in Gas Turbine
- Vol. 42, Issue 7, Pages: 838-842(2008)
- 作者机构：
  
  西安交通大学叶轮机械研究所,西安,710049
- 作者简介：
- 基金信息：
- DOI：
  CLC： TK474.7
- Online First：10 July 2008，
  
  Published：2008
- 稿件说明：
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杨佃亮, 丰镇平. Effects of Squealer Tip on Blade Aerodynamic Performance and Tip Heat Transfer in Gas Turbine[J]. 2008, 42(7): 838-842.
DOI：

杨佃亮, 丰镇平. Effects of Squealer Tip on Blade Aerodynamic Performance and Tip Heat Transfer in Gas Turbine[J]. 2008, 42(7): 838-842. DOI：

摘要

应用数值方法研究了燃气透平动叶顶部凹槽对动叶气动性能及叶顶传热的影响.采用商用计算流体力学软件CFX5.7求解稳态可压时均N-S方程组

湍流模型采用标准k-ω湍流模型

总体求解精度为二阶.计算叶型为一个典型现代燃气透平动叶片

叶顶凹槽深度取3%叶高

考虑了5种不同叶顶间隙的影响.结果表明:在凹槽内存在复杂的流动结构

相对平叶顶动叶

凹槽能够显著降低叶顶的泄漏流量

减小泄漏损失

尤其在大间隙时更为明显; 在小间隙时采用凹槽叶顶可以降低叶顶热负荷

而在大间隙时

凹槽叶顶的热负荷反而高于平叶顶的热负荷.

Abstract

Effects of squealer tips on blade aerodynamic performances and tip heat transfer in a gas turbine were investigated. CFD simulations were performed for both flat and squealer blade tips by solving steady compressible Reynolds-averaged N-S equations in conjunction with the standard k-ω two-equation turbulence model. The overall accuracy was of the second order. The blade calculated was a typical rotor blade in a modern gas turbine. The groove depth-blade span ratio was specified as 3%. The influences of five different tip gap-blade span ratios

e.g.

0.4%

0.7%

1.0%

1.3%

and 1.6%

were considered. The results show that

by comparison with the flat tip

the squealer tip can reduce the blade tip leakage flow and increase the blade aerodynamic efficiency

especially in the case of large gap. Moreover

the heat load of the squealer tip decreases for the small gap while increases for the large gap.

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references

祁明旭,丰镇平.透平动叶顶部间隙流的表现形式及其对透平性能的影响[J].西安交通大学学报,2005,39(3): 243-246.

QI Mingxu, FENG Zhenping. Representation formation of tip clearance flow and influence on turbine performance[J]. Journal of Xi'an Jiaotong University, 2005, 39(3):243-246.

DUNN M G. Convective heat transfer and aerodynamics in axial flow turbines[J]. ASME Journal of Turbomachinery, 2001, 123(4): 637-686.

BINDON J P. The measurement and formation of tip clearance loss[J]. ASME Journal of Turbomachinery, 1989, 111(2): 257-263.

KWAK J S, HAN Jechin. Heat transfer coefficients on the squealer tip and near squealer tip regions of a gas turbine blade[J]. ASME Journal of Turbomachinery, 2003, 125(4): 669-677.

NEWTON P J, LOCK G D, KRISHNABABU S K, et al. Heat transfer and aerodynamics of turbine blade tips in a linear cascade[J]. ASME Journal of Turbomachinery, 2006, 128(2): 300-309.

YANG Dianliang, FENG Zhenping. Tip leakage flow and heat transfer predictions for turbine blades[C]∥Proceedings of ASME Turbo Expo 2007. New York,USA:ASME, 2007: 589-596.

ROACHE P J. Perspective: a method for uniform reporting of grid refinement studies[J]. ASME Journal of Turbomachinery, 1994, 116:405-413.

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