尾缘开缝透平叶片内流动传热特性研究

高炎; 晏鑫; 李军

doi:10.7652/xjtuxb201810005

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尾缘开缝透平叶片内流动传热特性研究

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- 尾缘开缝透平叶片内流动传热特性研究
- Investigation on Characteristics of Flow and Heat Transfer in a Turbine Blade with Trailing-Edge Cutback
- 西安交通大学学报 2018年52卷第10期页码：31-40+48
- 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/xjtuxb201810005
  中图分类号： TK474.7
- 网络首发：2018-10-10，
  
  纸质出版：2018
- 稿件说明：
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高炎, 晏鑫, 李军. 尾缘开缝透平叶片内流动传热特性研究[J]. 西安交通大学学报, 2018,52(10):31-40+48.

Investigation on Characteristics of Flow and Heat Transfer in a Turbine Blade with Trailing-Edge Cutback[J]. 2018, 52(10): 31-40+48.
高炎, 晏鑫, 李军. 尾缘开缝透平叶片内流动传热特性研究[J]. 西安交通大学学报, 2018,52(10):31-40+48. DOI： 10.7652/xjtuxb201810005.

Investigation on Characteristics of Flow and Heat Transfer in a Turbine Blade with Trailing-Edge Cutback[J]. 2018, 52(10): 31-40+48. DOI： 10.7652/xjtuxb201810005.

摘要

采用带转捩的SST k-ω湍流模型

计算获得了不同来流条件和冷气质量流量比条件下

尾缘开缝透平叶片内的总压损失和传热系数

分析了尾缘开缝结构对叶片表面流动传热性能的影响

并与实验数据进行对比

验证了数值方法的有效性和精度。计算结果表明:与常规叶片相比

尾缘开缝叶片在冷气质量流量比为1.3%、2.6%和5.2%时

叶片吸力面喉部区域压力系数分别增大了0.1、0.15和0.2左右

出口气流角分别增大了0.3°、0.4°和0.5°左右; 尾缘开缝结构对叶片表面对流换热系数的影响区域主要位于吸力面喉部下游

与冷气质量流量比为1.3%的工况相比

尾缘开缝叶片在冷气质量流量比为2.6%和5.2%时

叶片尾缘吸力面侧对流换热系数分别增大了3%和5%左右; 开缝壁面上压力及对流换热系数均随着冷气质量流量比的增大逐渐增大

但当冷气流量一定时

在不同主流雷诺数条件下

开缝壁面上的对流换热系数基本一致; 冷气质量流量比为1.3%和2.6%时

尾缘开缝叶片总压损失比常规叶片高1%左右

当冷气质量流量比为5.2%时

主流总压损失低于常规叶片。

Abstract

The transition SST k-ω model is used to calculate the total pressure loss and heat transfer coefficients in a turbine blade with trailing edge cutback(gillslot)under different inflow conditions and ejection rates. The effects of the trailing edge cutback on the characteristics of flow and heat transfer in the gillslot blade are obtained and compared with the base vane without gillslot. The computing results of the pressure and heat transfer coefficients are compared with the experimental data to validate the present numerical methods. A comparison with the base vane shows that when the ejection rate is at 1.3%

2.6% and 5.2%

the pressure coefficient in the throat region of gillslot vane increases by 0.1

0.15 and 0.2

and the outlet flow angle in gillslot blades increases 0.3°

0.4° and 0.5°

respectively. The influence region of the cutback on heat transfer is mainly located at the downstream area near suction throat. When the ejection rate increases from 1.3% to 2.6% and 5.2%

the heat transfer coefficients on the suction surface of trailing edge increase by about 3% and 5%

respectively. As the ejection rate increases

the static pressure and the heat transfer coefficient on trailing edge cutback gradually increase. However

when the coolant mass flow rate is fixed

the heat transfer coefficients on the cutback surface are not sensitive to the mainstream Reynolds number. When the ejection rate is 1.3% and 2.6%

the total pressure loss in gillslot blade is about 1% higher than that in base vane

while the ejection rate increases to 5.2%

the total pressure loss in gillslot blade is lower than that in base vane.

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Keywords

references

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.

AMES F E, WANG C, BARBOT P A. Measurement and prediction of the influence of catalytic and dry low NOx combustor turbulence on vane surface heat transfer [J]. ASME Journal of Turbomachinery, 2003, 125(2): 221-231.

AMES F E, FIALA 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 [C]∥Proceedings of the 2007 ASME Turbo Expo. New York, USA: ASME, 2007: GT2007-27397.

AMES F E, JOHNSON J D, FIALA N J. Gill slot trailing edge aerodynamics-effects of blowing rate, Reynolds number, and external turbulence on aerodynamic losses and pressure distribution [C]∥Proceedings of the 2007 ASME Turbo Expo. New York, USA: ASME, 2007: GT2007-27399.

刘存良, 谢刚, 朱惠人. 高主流湍流度下倾斜角对圆柱孔气膜冷却特性影响的实验研究 [J]. 西安交通大学学报, 2018, 52(1): 1-7.

LIU Cunliang, XIE Gang, ZHU Huiren. Experimental research on the effect of hole inclined angle on the film cooling characteristics under high mainstream turbulence intensity [J]. Journal of Xi'an Jiaotong University, 2018, 52(1): 1-7.

朱惠人, 原和朋, 周志强, 等. 几何结构对后台阶缝隙气膜冷却效率的影响 [J]. 推进技术, 2006, 27(4): 312-315.

ZHU Huiren, YUAN Hepeng, ZHOU Zhiqiang, et al. Effect of geometry of back-step slot on film cooling [J]. Journal of Propulsion Technology, 2006, 27(4): 312-315.

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]. ASME Journal of Turbomachinery, 2001, 123(2): 249-257.

高丽敏, 刘波, 姜正礼, 等. 不同尾缘喷射对涡轮叶栅气动性能的影响 [J]. 推进技术, 2000, 21(2): 33-36.

GAO Limin, LIU Bo, JIANG Zhengli, et al. Aerodynamic effect of trailing edge coolant ejection on transonic turbine cascade [J]. Journal of Propulsion Technology, 2000, 21(2): 33-36.

王掩刚, 梅运焕, 刘波, 等. 计算涡轮叶片尾缘对开缝喷气的数值方法 [J]. 推进技术, 2002, 23(4): 315-317.

WANG Yangang, MEI Yunhuan, LIU Bo, et al. Numerical approach for turbine blade with trailing edge ejection [J]. Journal of Propulsion Technology, 2002, 23(4): 315-317.

KINGERY L B, SUZEN Y B, AMES F E. Computations of heat transfer in transitional turbine flows [C]∥Proceeding of 10th AIAA/ASME Joint Thermophysics Heat Transfer Conference. Reston, VA, USA: AIAA, 2010: 4325.

周超, 常海萍, 崔德平, 等. 斜劈缝涡轮导向叶片尾缘出流气体流动特性数值分析 [J]. 航空动力学报, 2006, 21(2): 268-274.

ZHOU Chao, XHANG Haiping, CUI Deping, et al. Numerical investigation of the cooling flow downstream of a turbine guide vane trailing edge slot [J]. Journal of Aerospace Power, 2006, 21(2): 268-274.

高炎, 晏鑫, 李军. 燃气透平叶片尾缘开缝结构冷却性能的数值研究 [J]. 西安交通大学学报, 2016, 50(3): 29-37.

GAO Yan, YAN Xin, LI Jun. Numerical investigations on film cooling performance of trailing edge cutback in gas turbine airfoil [J]. Journal of Xi'an Jiaotong University, 2016, 50(3): 29-37.

王瑞琴, 高炎, 晏鑫, 等. 燃气透平尾缘开缝区冷却性能的非定常研究 [J]. 西安交通大学学报, 2017, 51(12): 98-103.

WANG Ruiqin, GAO Yan, YAN Xin, et al. Numerical investigations on cooling performance of a gas turbine tailing edge cut-back [J]. Journal of Xi'an Jiaotong University, 2017, 51(12): 98-103.

吴凡,杜长河,王杰枫,等.周向喷嘴数对旋流冷却流动传热特性的影响.2018,52(7):94-100.[doi:10.7652/xjtuxb2018 07014]

税琳棋,黄博,董坤坤,等.燃气透平叶片树状分形内冷微通道的换热特性实验研究.2017,51(11):43-50.[doi:10.7652/xjtuxb201711007]

汤松臻,王飞龙,童自翔,等.烟气余热回收换热器积灰抑制技术研究及参数优化.2017,51(9):19-25.[doi:10.7652/xjtuxb201709003]

李劲劲,何坤,晏鑫,等.透平叶片近前缘端壁处换热性能的研究.2017,51(7):44-50.[doi:10.7652/xjtuxb201707007]

高炎,晏鑫,李军.燃气透平叶片尾缘开缝结构冷却性能的数值研究.2016,50(3):29-37.[doi:10.7652/xjtuxb201603005]

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