Investigations of Flow and Heat Transfer Performance in a Blade with Trailing-Edge Cutback and Lands

doi:10.7652/xjtuxb202001019

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Investigations of Flow and Heat Transfer Performance in a Blade with Trailing-Edge Cutback and Lands

更新时间：2025-07-09

- Investigations of Flow and Heat Transfer Performance in a Blade with Trailing-Edge Cutback and Lands
- Vol. 54, Issue 1, Pages: 150-161+183(2020)
- 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/xjtuxb202001019
  CLC： TK474.7
- Online First：10 January 2020，
  
  Published：2020
- 稿件说明：
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Investigations of Flow and Heat Transfer Performance in a Blade with Trailing-Edge Cutback and Lands[J]. 2020, 54(1): 150-161+183.
DOI：

Investigations of Flow and Heat Transfer Performance in a Blade with Trailing-Edge Cutback and Lands[J]. 2020, 54(1): 150-161+183. DOI： 10.7652/xjtuxb202001019.

摘要

针对燃气透平带肋板的尾缘开缝叶片

采用RANS(Reynolds Averaged Navier-Stokes)方程求解结合SST γ-Re

转换模型数值方法

研究了3种来流湍流度、3种来流雷诺数和3种冷气质量流量比条件下叶片和尾缘开缝区域的流动传热性能

并与无肋板开缝叶片进行了对比

利用实验数据考核了数值方法的有效性。计算结果表明:随着来流湍流度的增大

带肋板的尾缘开缝叶片表面传热系数逐渐增大

开缝壁面的传热系数基本不变

能量损失系数和总压损失系数随之增加; 在相同来流湍流度时

增加来流雷诺数可降低损失; 增大冷气质量流量比对叶片表面的传热系数影响很小

但可显著提升开缝壁面的传热系数; 与无肋板的开缝叶片相比

带肋板的尾缘开缝叶片表面的传热系数和压力系数更低

开缝壁面换热系数更高; 当Re为2.0×10

时

带肋板的开缝壁面平均换热系数比无肋板时的高14.46%

来流雷诺数分别为0.5×10

、1.0×10

、2.0×10

时

相比无肋板开缝叶片

带肋板尾缘开缝叶片的能量损失系数分别增加了3.75%、5.91%、6.75%

总压损失系数分别降低了3.4%、3.37%、2.06%。

Abstract

RANS(Reynolds-averaged Navier-Stokes)equations combined with transition model SST --Re

are adopted to investigate the flow and heat transfer performance in a gas turbine blade with trailing edge cutback and lands. At three inflow turbulence intensities

three mainstream Reynolds numbers and three coolant ejection rates

heat transfer coefficient distributions and aerodynamic loss in blade with trailing-edge cutback and lands are compared with those in trailing-edge cutback blade without lands. With the existing experimental data

the

reliability of numerical methods is validated at a range of operation conditions. The results show that

as the inflow turbulence intensity increases

heat transfer coefficients on blade surface for the blade with lands are gradually increased. However

the heat transfer coefficients on trailing edge cutback are not sensitive to the variations of inflow turbulence intensity. The energy loss coefficient and total pressure loss coefficient in b

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Keywords

references

HORBACH T T, SCHULZ A A, BAUER H J. Trailing edge film cooling of gas turbine airfoils-external cooling performance of various internal pin fin configurations [J]. Journal of Turbomachinery, 2011, 133(4): 041006.

SCHOBEIRI T, PAPPU K. Optimization of trailing edge ejection mixing losses: a theoretical and experimental study [J]. Journal of Fluids Engineering, 1999, 121(1): 118-125.

UZOL O, CAMCI C. Aerodynamic loss characteristics of a turbine blade with trailing edge coolant ejection: part 2 External aerodynamics, total pressure losses, and predictions [J]. Journal of Turbomachinery, 2001, 123(2): 249-257.

MARTINI P, SCHULZ A, BAUER H J, et al. Film cooling effectiveness and heat transfer on the trailing edge cut-back of gas turbine airfoils with various internal cooling designs [J]. Journal of Turbomachinery, 2006, 128(1): 196-205.

MARTINI P, SCHULZ A, BAUER H J, et al. Detached eddy simulation of film cooling performance on the trailing edge cut-back of gas turbine airfoils [J]. Journal of Turbomachinery, 2006, 128(2): 292-299.

BARIGOZZI G, PERDICHIZZI A, RAVELLI S. Pressure side and cutback trailing edge film cooling in a linear nozzle vane cascade at different Mach numbers [J]. Journal of Turbomachinery, 2012, 134(5): 051037.

BARIGOZZI G, ARMELLINI A, MUCIGNAT C, et al. Experimental investigation of the effects of blowing conditions and Mach number on the unsteady behavior of coolant ejection through a trailing edge cutback [J]. International Journal of Heat and Fluid Flow, 2012, 37: 37-50.

BARIGOZZI G, RAVELLI S, ARMELLINI A, et al. Effects of injection conditions and Mach number on unsteadiness arising within coolant jets over a pressure side vane surface [J]. International Journal of Heat and Mass Transfer, 2013, 67: 1220-1230.

ABDEH H, BARIGOZZI G. A parametric investigation of vane pressure side cutback film cooling by dual luminophor PSP [J]. International Journal of Heat and Fluid Flow, 2018, 69: 106-116.

曾军, 乔渭阳, 孙大伟, 等. 带尾缘劈缝冷气喷射的涡轮叶栅性能实验及计算 [J]. 推进技术, 2008, 29(6): 710-715.

ZENG Jun, QIAO Weiyang, SUN Dawei, et al. Numerical simulation and experiment for turbine cascade with trailing edge coolant injection [J]. Journal of Propulsion Technology, 2008, 29(6): 710-715.

姚世传, 施鎏鎏, 刘正, 等. 叶片尾缘冷气喷射气动与传热性能分析 [J]. 热能动力工程, 2018, 33(5): 47-54.

YAO Shichuan, SHI Liuliu, LIU Zheng, et al. Analysis of aerodynamic and heat transfer performance of the blade trailing edge ejection [J]. Journal of Engineering for Thermal Energy and Power, 2018, 33(5): 47-54.

高炎, 晏鑫, 李军. 尾缘开缝透平叶片内流动传热性能研究 [J]. 西安交通大学学报, 2018, 52(10): 31-40.

GAO Yan, YAN Xin, LI Jun. Investigation on Characteristics of flow and heat transfer in a turbine blade with trailing-edge cutback [J]. Journal of Xi’an Jiaotong University, 2018, 52(10): 31-40.

CAKAN M, TASLIM M E. Experimental and numerical study of mass/heat transfer on an airfoil trailing-edge slots and lands [J]. Journal of Turbomachinery, 2007, 129(2): 281-293.

AMES F E, FIALI N J, JOHNSON J D. Gill slot trailing edge heat transfer-effects of blowing rate, Reynolds number, and external turbulence on heat transfer and film cooling effectiveness: GT2007-27397 [R]. New York, USA: ASME, 2007: 351-362.

JOHNSON J D, FIALA N J, AMES F E. Gill slot trailing edge aerodynamics: effects of blowing rate, Reynolds number, and external turbulence on aerodynamic losses and pressure distribution [J]. Journal of Turbomachinery, 2008, 131(1): 011016.

FIALA N J, JASWAL I, AMES F E. Letterbox trailing edge heat transfer: effects of blowing rate, Reynolds number, and external turbulence on heat transfer and film cooling effectiveness [J]. Journal of Turbomachinery, 2010, 132(1): 011017.

FIALA N J, JOHNSON J D, AMES F E. Aerodynamics of a letterbox trailing edge-effects of blowing rate, Reynolds number, and external turbulence on aerodynamic losses and pressure distribution [J]. Journal of Turbomachinery, 2010, 132(4): 041011.

HORBACH T, SCHULZ A, BAUER H J. Trailing edge film cooling of gas turbine airfoils-effects of ejection lip geometry on film cooling effectiveness and heat transfer [J]. Heat Transfer Research, 2010, 41(8): 849-865.

GURRAM N, IRELAND P T, WONG T H, et al. Study of film cooling in the trailing edge region of a turbine rotor blade in high speed flow using pressure sensitive paint [C]∥Proceedings of the 2016 ASME Turbo Expo. New York, USA: ASME, 2016: GT2016-57356.

KINGEY L B, SUZEN Y B, AMES F E. Computations of heat transfer in transitional turbine flows [C]∥Proceedings of 10th AIAA/ASME Joint Thermo-physics Heat Transfer Conference. New York, USA: AIAA, 2010: 4325.

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