Unsteady Investigations on Cooling Performance of a Gas Turbine Tailing Edge Cut-Back

doi:10.7652/xjtuxb201712015

您当前的位置：

首页 >

文章列表页 >

Unsteady Investigations on Cooling Performance of a Gas Turbine Tailing Edge Cut-Back

更新时间：2025-07-09

- Unsteady Investigations on Cooling Performance of a Gas Turbine Tailing Edge Cut-Back
- Vol. 51, Issue 12, Pages: 98-103(2017)
- 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/xjtuxb201712015
  CLC： TK474.7
- Online First：10 December 2017，
  
  Published：2017
- 稿件说明：
移动端阅览
Unsteady Investigations on Cooling Performance of a Gas Turbine Tailing Edge Cut-Back[J]. 2017, 51(12): 98-103.
DOI：

Unsteady Investigations on Cooling Performance of a Gas Turbine Tailing Edge Cut-Back[J]. 2017, 51(12): 98-103. DOI： 10.7652/xjtuxb201712015.

摘要

采用分离涡模拟(DES)非定常数值计算方法

对3种吹风比(M为0.5、0.8、1.1)、3种肋柱结构(双列长肋G1、针肋G2a、针肋G2b)条件下燃气透平尾缘开缝区域的冷却性能进行了数值研究

并将计算得到的肋柱下游绝热壁面的展向平均冷却效率与实验结果进行了对比。实验结果表明

与RANS(雷诺平均N-S方程)方法相比

DES非定常求解能获得较为准确的绝热壁面冷却效率分布。在3种吹风比条件下

肋柱下游壁面的展向平均冷却效率沿流向方向先上升

在达到最大值后迅速下降。吹风比为0.8时

在肋柱中间截面的下游

冷却气膜覆盖的轴向距离最远

但冷却效果好的区域(温度低于310 K)面积最小。对于3种肋柱结构

在肋柱下游后半段冷却效率都会出现较大的下降

且唇缘处都出现了周期性的涡流脱落

涡流结构与肋柱的几何结构密切相关。与双列长肋G1相比

针肋结构(G2a、G2b)下游的绝热壁面温度分布均匀

G2b针肋下游的绝热壁面上所覆盖的冷却气膜厚度和稳定性都优于其他2种结构。

Abstract

The film cooling performance in a gas turbine trailing edge cut-back region is numerically investigated by using the unsteady Detached-Eddy-Simulation(DES)method. The laterally-averaged cooling effectiveness on the adiabatic wall at the downstream of ribs is predicted at three blowing ratios(M=0.5

0.8

1.1)and three rib-array configurations(double in-line rib array G1

pin-fin array G2a and pin-fin array G2b)

and numerical results are compared with measurement data. Results and a comparison with the steady RANS(Reynolds-averaged Navier-Stokes equations)show that

the unsteady DES method has a superior accuracy in predicting the film cooling effectiveness distributions on the adiabatic wall at the downstream of ribs. The laterally-averaged cooling effectiveness on the wall at the downstream of ribs goes up along the streamwise direction and then goes down sharply after reaching the maximum value at three blowing ratios. When M=0.8

the coolant coverage on the adiabatic wall along the axial direction reaches the farthest among three blowing ratio cases

and is occurred just at the downstream middle region of ribs. However

the area with better film cooling effectiveness(temperature below 310 K)is the smallest among the three blowing ratio cases. The film cooling effectiveness significantly decreases on the rear part of the adiabatic wall for three rib-array configurations

and the periodical vortex shedding is appeared at the downstream of the blunt lip. It indicates that the vortex shedding structures are closely related to geometrical configuration of the rib-array. The temperature distributions on the adiabatic wall downstream of ribs are much uniform for the pin-fin ribs(G2a and G2b). Among three rib-array configurations

G2b performs better than the other two designs in both the film cooling thickness and the stability in the trailing edge cut-back region.

关键词

Keywords

references

UZOL O, CANCI C. Aerodynamic loss characteristics of a turbine blade with trailing edge coolant ejection: Part 2 external aerodynamics, total pressure losses, and predictions [J]. ASME Journal of Turbomachinery, 2001, 123: 249-257.

王文三, 唐菲, 秦立森, 等. 涡轮静叶尾缘开槽冷却特性的数值研究 [J]. 工程热物理学报, 2010, 31(12): 2005-2008.

WANG Wensan, TANG Fei, QIN Lisen, et al. Numerical study on slotted cooling characteristics of turbine trailing edge [J]. ASME Journal of Engineering Thermophysics, 2010, 31(12): 2005-2008.

周超, 常海萍, 崔德平, 等. 涡轮叶片尾缘斜劈缝气膜冷却数值模拟 [J]. 南京航空航天大学学报, 2006, 38(5): 583-589.

ZHOU Chao, CHANG Haiping, CUI Deping, et al. Numerical investigation of the cooling flow downstream of a turbine guide vane trailing edge slot [J]. Journal of Nanjing University of Aeronautics and Astronautics, 2006, 38(5): 583-589.

MAREK C J, TAKINA R. Effect of free stream turbulence on film cooling: TN D-7958 [R]. Washington, D.C., USA: NASA, 1975: 1-27.

TASLIM M E, SPRING S D, MEHLMANN B P, et al. An experimental investigation of film cooling effectiveness for slots of various exit geometries [J]. Journal of Thermophysics and Heat Transfer, 1992, 6(2): 302-307.

HOLLOWAY D S, LEYLEK J H, BUCK F A, et al. Pressure side bleed film cooling: Part 1 steady framework for experimental and computational results: GT2002-30471 [R]. New York, USA: ASME, 2002.

HOLLOWAY D S, LEYLEK J H, BUCK F A. Pressure side bleed film cooling: Part 2 unsteady framework for experimental and computational results: GT2002-30472 [R]. New York, USA: ASME, 2002.

周建兴, 陶智, 吴宏, 等. 涡轮叶片尾缘复合冷却通道换热的数值模拟 [J]. 北京航空航天大学学报, 2004, 30(2): 147-151.

ZHOU Jianxing, TAO Zhi, WU Hong, et al. Numerical simulation of heat exchange in composite trains of turbine blade trailing edge [J]. Journal of Beijing University of Aeronautics and Astronautics, 2004, 30(2): 147-151.

宋双文, 胡好生, 杨卫华, 等. 肋柱对叶片尾缘对流换热特性的影响 [J]. 航空动力学报, 2007, 22(10): 1604-1608.

SONG Shuangwen, HU Haosheng, YANG Weihua, et al. Effects of ribs on convective heat transfer characteristics of turbine blade trailing edge [J]. Journal of Aerospace Power, 2007, 22(10): 1604-1608.

MARTINI P, SCHULZ A. Experimental and numerical investigation of trailing edge film cooling by circular wall jets ejected from a slot with internal rib arrays [J]. ASME Journal of Turbomachinery, 2004, 126(2): 229-236.

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]. ASME 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]. ASME Journal of Turbomachinery, 2006, 128(2): 292-299.

Views

下载量

CSCD

Alert me when the article has been cited

提交

Tools

Publicity Resources

Optimization of Full-Endwall Non-Axisymmetric Contouring Design for Turbine Cascades Aimed at Enhancing Film Cooling Effectiveness

Investigation on Film Cooling Performance of the Squealer Tip with Baffle in a Linear Turbine Cascade

Numerical Investigations on the Cooling Performance of Trailing Edge Cutback in Gas Turbine Blade

Numerical Simulation for Flow and Heat Transfer Characteristics of Impingement/Effusion Cooling on a Flat Plane

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

Related Author

TAO Zhi

WANG Jie

LI Bolin

YAN Yifei

SONG Liming

LI Jun

FENG Zhenping

LIU Yudong

Related Institution

School of Energy and Power Engineering, Xi’an Jiaotong University

TaiHang Laboratory

China United Gas Turbine Technology Co., Ltd.

Institute of Turbomachinery, Xi'an Jiaotong University

(School of Energy and Power Engineering, Xi'an Jiaotong University,,)

⁰