Influence of axially⁃convergent contouring on cascade endwall film cooling characteristics in gas turbine

Bo BAI; Zhigang LI; Jun LI

doi:10.13224/j.cnki.jasp.20210183

Chinese

您当前的位置：

首页 >

文章列表页 >

Influence of axially⁃convergent contouring on cascade endwall film cooling characteristics in gas turbine

Turbomachinery | 更新时间：2025-04-07

- Influence of axially⁃convergent contouring on cascade endwall film cooling characteristics in gas turbine
- Journal of Aerospace Power Vol. 37, Issue 5, Pages: 1042-1053(2022)
- 作者机构：
  
  1.西安交通大学能源与动力工程学院，西安 710049
  2.先进航空发动机协同创新中心，北京 100191
- 作者简介：
- 基金信息：
- DOI：10.13224/j.cnki.jasp.20210183
  CLC：
- 稿件说明：
移动端阅览
Bo BAI, Zhigang LI, Jun LI. Influence of axially⁃convergent contouring on cascade endwall film cooling characteristics in gas turbine[J]. Journal of Aerospace Power, 2022, 37(5): 1042-1053.
DOI：

Bo BAI, Zhigang LI, Jun LI. Influence of axially⁃convergent contouring on cascade endwall film cooling characteristics in gas turbine[J]. Journal of Aerospace Power, 2022, 37(5): 1042-1053. DOI： 10.13224/j.cnki.jasp.20210183.

摘要

为有效评估轴向收敛造型对端壁气膜冷却性能的影响，数值研究了不同吹风比下，轴向收敛造型对跨声速燃气涡轮叶栅端壁上游双排离散孔绝热气膜冷却效率的影响。模拟某工业燃气涡轮真实运行工况（进口湍流度为16%、出口马赫数为0.85、出口雷诺数为1.5×10

），采用基于“两类热边界条件”模型的壁面传热系数和绝热冷却效率数值预测方法，比较分析了3种吹风比（1.0、2.5、3.5）下，简化平板端壁结构和轴向收敛造型端壁结构的端壁热负荷分布、绝热气膜冷却效率分布和近端壁二次流场结构，以及端壁上游气膜孔射流对叶片表面的二次冷却作用（幻影冷却）。结果表明：轴向收敛造型可以削弱马蹄涡强度，降低端壁热负荷，尤其是叶片肩部区域；轴向收敛造型可以显著增加端壁气膜覆盖范围和绝热气膜冷却效率，尤其在叶片前缘和压力面等难以冷却区域；随吹风比增加，轴向收敛造型对端壁气膜冷却特性的影响效果先增加后减小，在设计吹风比为2.5时，轴向收敛造型对端壁绝热气膜冷却效率的增强效果最显著（增加约35%）；轴向收敛造型显著增加叶片前缘和压力面幻影冷却面积，尤其是叶片前缘附近面积增加约100%（设计吹风比下，冷却区域达0.1倍叶高），可有效减小叶片冷却的冷气需求流量。轴对称收敛端壁造型是进一步提高燃气涡轮叶栅端壁绝热气膜冷却效率、减小冷气流量，实现端壁高效冷却布局的有效技术途径。

Abstract

In order to evaluate the influences of the axially⁃convergent contouring on the endwall film cooling performance of the upstream double⁃row film holes，the cascade endwall adiabatic film cooling effectiveness was predicted through numerical simulation.The endwall thermal load distribution，adiabatic film cooling effectiveness distribution and secondary flow field were calculated and analyzed for two endwall configurations （flat endwall and axially convergent contoured endwall） at three different blowing ratios （1.0，2.5，3.5） under the simulated realistic operation condition of an industrial gas turbine，inlet turbulence of 16%，exit Mach number of 0.85，exit Reynolds number of 1.5×10

，based on “two types of thermal boundaries” numerical method.Simultaneously，the secondary cooling （phantom cooling） phenomenon of the upstream purge flow on the vane surface was noticed.Results showed that compared with the flat end⁃wall configuration，the axially⁃convergent contoured endwall reduced the strength of the horse⁃shoe vortex and endwall thermal load，especially at the region of vane suction surface shoulder.For the axially⁃convergent contoured endwall，the upstream coolant jets were more efficiently targeted at the endwall，yielding higher endwall adiabatic film cooling effectiveness，especially at the regions of the vane leading edge and vane pressure side where cooling was harder due to the stronger secondary flow.At the increasing blowing ratio，the effects of axially⁃convergent contouring on endwall film cooling first increased and then decreased.The axially⁃convergent contouring resulted in a significant increase （up to 35%） in end⁃wall adiabatic film cooling effectiveness at design blowing ratio of 2.5.The axially⁃convergent contouring obviously increased the phantom cooling size around the vane leading edge and pressure surface，especially at the region around the vane leading edge （up to 100%，0.1 span at design blowing ratio）.This led to an obvious reduction in the demand of coolant.Therefore，the axially⁃convergent contoured endwall is an effective approach to increase the endwall adiabatic film cooling effectiveness，reduce the demand of coolant and realize the efficient endwall cooling scheme.

关键词

Keywords

references

TOM I P , YANG S V . Turbine aerodynamics,heat transfer,materials,and mechanics [M]. Reston,VA,US : American Institute of Aeronautics and Astronautics （AIAA） , 2014 .

李雪英 , 任静 , 蒋洪德 . 燃烧室温度剖面对静叶端壁冷却的影响 [J]. 工程热物理学报 , 2015 , 36 （ 4 ）: 752 ⁃ 755 .

LI Xueying , REN Jing , JIANG Hongde . The influence of temperature profile of combustor on the cooling of static blade wall [J]. Journal of Engineering Thermal Physics , 2015 , 6 （ 4 ）: 752 ⁃ 755 . （in Chinese）

张魏 , 金文 . 燃气轮机冷却技术综述 [J]. 燃气轮机技术 , 2008 , 21 （ 1 ）: 24 ⁃ 27 .

ZHANG Wei , JING Wen . Summary of gas turbine cooling technology [J]. Journal of Gas Turbine Technology , 2008 , 21 （ 1 ）: 24 ⁃ 27 . （in Chinese）

李志刚 , 白波 , 刘璐萱 , 等 . 进口不重合和轴对称造型对跨声速涡轮叶栅端壁传热特性的影响 [J]. 航空动力学报 , 2019 , 34 （ 12 ）: 2695 ⁃ 2705 .

LI Zhigang , BAI Bo , LIU Luxuan , et al . Effects of inlet misalignment and axisymmetric contouring on endwall heat transfer characteristics in transonic turbine cascade [J]. Journal of Aerospace Power , 2019 , 34 （ 12 ）: 2695 ⁃ 2705 . （in Chinese）

BURD S W , SIMON T W . Flow measurements in a nozzle guide vane passage with a low aspect ratio and endwall contouring [J]. Journal of Turbomachinery , 2000 , 122 （ 4 ）: 659 ⁃ 666 .

SHIH T I P , LIN Y L . Controlling secondary⁃flow structure by leading⁃edge airfoil fillet and inlet swirl to reduce aerodynamic loss and surface heat transfer [J]. Journal of Turbomachinery , 2003 , 125 （ 1 ）: 48 ⁃ 56 .

HARTHAND J C , GREGORY⁃SMITH D G , HARVEY N W , et al . Non⁃axisymmetric turbine end wall design:Part Ⅱ experimental validation [J]. Journal of Turbomachinery , 2000 , 122 （ 2 ）: 286 ⁃ 293 .

李国君 , 马晓永 , 李军 . 非轴对称端壁成型及其对叶栅损失影响的数值研究 [J]. 西安交通大学学报 , 2005 ， 39 （ 11 ）: 9 ⁃ 12 .

LI Guojun , MA Xiaoyong , LI Jun . Non⁃axisymmetric turbine end wall profiling and numerical investigation of its effect on the turbine cascade loss [J]. Journal of Xi'an Jiaotong University , 2005 ， 39 （ 11 ）: 9 ⁃ 12 . （in Chinese）

孙皓 , 宋立明 , 李军 . 透平叶栅非轴对称端壁优化设计 [J]. 西安交通大学学报 , 2013 , 47 （ 9 ）: 35 ⁃ 40 .

SUN Hao , SONG Liming , LIU Jun . Optimization design of nonaxisymmetrical end wall profiling for turbine cascade [J]. Journal of Xi'an Jiaotong University , 2013 , 47 （ 9 ）: 35 ⁃ 40 . （in Chinese）

斯夏依 , 羌晓青 , 滕金芳 , 等 . 非轴对称端壁改善涡轮叶栅流场研究 [J]. 工程热物理学报 , 2017 , 38 （ 5 ）: 970 ⁃ 977 .

SI Xiayi , QIANG Xiaoqing , TENG Jinfang , et al . Investigation of improving the turbine cascade flow using non⁃axisymmetric endwall contouting [J]. Journal of Engineering Thermal Physics , 2017 , 38 （ 5 ）: 970 ⁃ 977 . （in Chinese） .

唐慧敏 , 刘帅强 , 罗华玲 . 涡轮平面叶栅非轴对称端壁优化设计 [J]. 航空动力学报 , 2015 , 30 （ 3 ）: 707 ⁃ 713 .

TANG Huiming , LIU Shuaiqiang , LUO Hualing . Optimal design of profiled endwall for turbine cascade [J]. Journal of Aerospace Power , 2015 , 30 （ 3 ）: 707 ⁃ 713 . （in Chinese）

LYNCH S P , SUNDARAM N , THOLE K.A , et al . Heat transfer for a turbine blade with non⁃axisymmetric endwall contouring [J]. Journal of Turbomachinery , 2011 , 133 （ 1 ）: 011019.1 ⁃ 011019.9 .

YANG C S . LIN C L,GAU C.Film cooling performance and heat transfer over an inclined film⁃cooled surface [J]. Journal of Thermophysics and Heat Transfer , 2008 , 22 （ 3 ）: 485 ⁃ 492 .

THRIFT A A , THOLE K A , HADA S . Effects of an axisymmetric contoured endwall on a nozzle guide vane:adiabatic effectiveness measurements [J]. Journal of Turbomachinery , 2011 ， 133 （ 4 ）: 041007.1 ⁃ 041007.10 .

陶志，武晓龙，祝培源，等 . 非轴对称端壁造型对叶片端壁气热性能影响的研究 [J]. 推进技术 , 2019 , 40 （ 8 ）： 1734 ⁃ 1742 .

TAO Zhi , WU Xiaolong , ZHU Peiyuan , et al . Research on effects of nonaxisymmetric endwall contouring on blade endwall aerothermal performance [J]. Journal of Propulsion Technology , 2019 , 40 （ 8 ）: 1734 ⁃ 1742 . （in Chinese）

MAHMOOD G I , GUSTAFSON R , ACHARYA S . Flow dynamics and film cooling effectiveness on a non⁃axisymmetric contour endwall in a two⁃dimensional cascade passage [R]. Orlando,Florida,US:Turbo Expo:Power for Land,Sea,and Air , 2009 .

OKITA Y , NAKAMATA C . Computational predictions of endwall film cooling for a turbine nozzle vane with an asymmetric contoured passage [R]. Berlin,Germany:Turbo Expo:Power for Land,Sea,and Air , 2008 .

LUEHR L , SIBOLD R , MAO S , et al . The effect of step misalignment on purge flow cooling of nozzle guide vane at transonic conditions [J]. Journal of Turbomachinery , 2020 , 142 （ 10 ）: 101004.1 ⁃ 101004.10 .

Views

下载量

CSCD

Alert me when the article has been cited

提交

Tools

Publicity Resources

Film cooling performance and flow resistance characteristics of single/triple⁃row fan⁃shaped holes based on actual density ratio

Film cooling performance of fan-shaped film hole on blade pressure side in linear transonic cascade

Effect of rotation on the leading-edge region film cooling of a twisted turbine blade

Test on effect of wake on film cooling for turbine blade withdust-pan shaped holes

Experimental and numerical studies on the film cooling characteristics of anisotropic composite plates

Related Author

Yingqing ZU

Hong WEI

ZHU Huiren

LUO Jianxia

LI Jie

陶智

马薏文

李海旺

Related Institution

School of Mechanical Engineering，Shanghai Jiao Tong University

Department of Aeronautics and Astronautics，Fudan University

先进航空发动机协同创新中心

北京航空航天大学能源与动力工程学院航空发动机气动热力国家级重点实验室

西北工业大学动力与能源学院

AI问答

Postal code：100079
Tel：（010）53879206 Email：tmw@bjxintong.com.cn
Technical support is provided by Beijing Founder electronics co., LTD 京ICP备09082226号-64 京公网安备11010602201714号
It is recommended to read the content of this site in Chrome&IE9+. Please switch to extreme mode in browser 360.
Cookies We use cookies to help provide and enhance our service and tailor content. By continuing, you agree to the use of cookies.

⁰