平面叶栅多凹槽叶顶倾斜圆柱孔气膜冷却与气动特性研究

贾哲; 李冯; 张韦馨; 刘钊; 石; 丰镇平

doi:10.7652/xjtuxb202309002

您当前的位置：

首页 >

文章列表页 >

平面叶栅多凹槽叶顶倾斜圆柱孔气膜冷却与气动特性研究

能源与动力 | 更新时间：2025-07-09

- 平面叶栅多凹槽叶顶倾斜圆柱孔气膜冷却与气动特性研究
- Investigation on Film Cooling and Aerodynamic Performance of the Multi-Cavity Tip with Inclined Film Holes in a Linear Turbine Cascade
- 西安交通大学学报 2023年57卷第9期页码：10-21
- 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：
  
  : 2023-02-09。作者简介: 贾哲(1997—),男,博士生
  刘钊(通信作者),男,副教授。基金项目: 国家科技重大专项资助项目(2017-III-0009-0035)。
- 基金信息：
  
  : 2023-02-09。作者简介: 贾哲(1997—),男,博士生;刘钊(通信作者),男,副教授。基金项目: 国家科技重大专项资助项目(2017-III-0009-0035)。
- DOI：10.7652/xjtuxb202309002
  中图分类号： V231.1
- 网络首发：2023-09-10，
  
  纸质出版：2023
- 稿件说明：
移动端阅览
贾哲, 李冯, 张韦馨, 等. 平面叶栅多凹槽叶顶倾斜圆柱孔气膜冷却与气动特性研究[J]. 西安交通大学学报, 2023,57(9):10-21.

JIA Zhe, LI Feng, ZHANG Weixin, et al. Investigation on Film Cooling and Aerodynamic Performance of the Multi-Cavity Tip with Inclined Film Holes in a Linear Turbine Cascade[J]. 2023, 57(9): 10-21.
贾哲, 李冯, 张韦馨, 等. 平面叶栅多凹槽叶顶倾斜圆柱孔气膜冷却与气动特性研究[J]. 西安交通大学学报, 2023,57(9):10-21. DOI： 10.7652/xjtuxb202309002.

JIA Zhe, LI Feng, ZHANG Weixin, et al. Investigation on Film Cooling and Aerodynamic Performance of the Multi-Cavity Tip with Inclined Film Holes in a Linear Turbine Cascade[J]. 2023, 57(9): 10-21. DOI： 10.7652/xjtuxb202309002.

摘要

为提高燃气透平动叶叶顶的气膜冷却有效度

并减少由叶顶泄漏流引起的气动损失

对带倾斜圆柱孔的多凹槽叶顶冷却与气动特性进行了研究

试验测量了多凹槽叶顶的气膜冷却特性

并对其气动特性进行了数值模拟分析。首先采用压力敏感漆技术

在4种吹风比(0.5、1.0、1.5和2.0)下

测量了4种多凹槽叶顶(凹槽数分别为1、2、3和4个)气膜冷却性能的变化规律; 然后经湍流模型验证

采用与试验数据吻合最好的SST k-ω模型

分析了多凹槽叶顶的流场结构及气动损失。研究结果表明:多凹槽叶顶在叶顶区域前、中部具有更优良的气膜冷却有效度

同时对肩壁也有良好保护作用; 由于多凹槽叶顶的肋能够阻挡冷气向下游流动

肋后能形成涡卷吸冷气

因而能够提高肋前和肋后的气膜冷却有效度; 相较于单凹槽叶顶

多凹槽叶顶的气动损失较低

其中三凹槽叶顶的总压损失系数最小

最多比单凹槽叶顶的低9.3%。

Abstract

In order to improve the film cooling effectiveness and reduce the aerodynamic loss of the gas turbine blade tips

an experiment was conducted to investigate the film cooling characteristics of the multi-cavity tips with inclined film holes

and the aerodynamic performance of these tips was numerically simulated. Firstly

the variation rule of the film cooling performance of four types of multi-cavity tips

of which the cavity number was one

two

three and four respectively

was measured under four blowing ratios(0.5

1.0

1.5 and 2.0)by the pressure sensitive paint technique. Secondly

after the validation of turbulence models

the SST k-ω turbulence model

which showed the most excellent agreement with experimental results

was adopted to simulate the flow field structure and aerodynamic loss of the multi-cavity tips. The results show that the multi-cavity tips have better film cooling coverage on the front and middle parts of the tips as well as the rims; the installed ribs of the multi-cavity tips can prevent the coolant from flowing downstream and induce vortices behind the ribs to involve the coolant

leading to better film cooling effectiveness on the upstream and downstream parts of the ribs; compared with the conventional cavity tips

the aerodynamic loss of the multi-cavity tips are lower

of which the three-cavity tips performs the lowest loss coefficient and it is 9.3% lower than that of the conventional cavity tip at most.

关键词

Keywords

references

高杰, 郑群, 岳国强, 等. 燃气轮机涡轮叶顶间隙气热技术研究进展 [J]. 航空学报, 2017, 38(9): 71-101.

GAO Jie, ZHENG Qun, YUE Guoqiang, et al. Research progress on turbine blade tip aerodynamics and heat transfer technology for gas turbines [J]. Acta Aeronautica et Astronautica Sinica, 2017, 38(9): 71-101.

AHN J, MHETRAS S, HAN J C. Film-cooling effectiveness on a gas turbine blade tip using pressure-sensitive paint [J]. Journal of Heat Transfer, 2005, 127(5): 521-530.

AZAD G S, HAN J C, BOYLE R J. Heat transfer and flow on the squealer tip of a gas turbine blade [J]. Journal of Turbomachinery, 2000, 122(4): 725-732.

KANG D B, LEE S W. Effects of squealer rim height on heat/mass transfer on the floor of cavity squealer tip in a high turning turbine blade cascade [J]. International Journal of Heat and Mass Transfer, 2016, 99: 283-292.

SENEL C B, MARAL H, KAVURMACIOGLU L A, et al. An aerothermal study of the influence of squealer width and height near a HP turbine blade [J]. International Journal of Heat and Mass Transfer, 2018, 120: 18-32.

LI Chenxi, XIANG Jiacheng, SONG Liming, et al. An aerothermal analysis of the effects of tip gap height and cavity depth of a gas turbine blade [J]. International Journal of Thermal Sciences, 2020, 158: 106521.

SAKAOGLU S, KAHVECI H S. Effect of cavity depth on thermal performance of a cooled blade tip under rotation [J]. International Journal of Heat and Mass Transfer, 2019, 143: 118561.

ZHU Diwei, ZHANG Qiang, LU Shaopeng, et al. Relative casing motion effect on squealer tip cooling performance at tight tip clearance [J/OL]. Journal of Thermal Science and Engineering Applications, 2020: 1-18[2023-02-01]. https://doi.org/10.1115/1.4046518.

杨佃亮, 丰镇平. 叶顶凹槽对燃气透平动叶气动性能及叶顶传热的影响 [J]. 西安交通大学学报, 2008, 42(7): 838-842.

YANG Dianliang, FENG Zhenping. Effects of squealer tip on blade aerodynamic performance and tip heat transfer in gas turbine [J]. Journal of Xi'an Jiaotong University, 2008, 42(7): 838-842.

杜昆, 李军. 涡轮叶片凹槽状叶顶非定常流动传热特性的数值研究 [J]. 推进技术, 2017, 38(3): 551-558.

DU Kun, LI Jun. Numerical investigations on unsteady leakage flow and heat transfer characteristics of turbine blade with squealer tip [J]. Journal of Propulsion Technology, 2017, 38(3): 551-558.

周治华, 陈绍文, 李伟航, 等. 叶顶凹槽间隙气膜冷却的传热数值研究 [J]. 推进技术, 2018, 39(3): 575-582.

ZHOU Zhihua, CHEN Shaowen, LI Weihang, et al. Heat transfer numerical research on film cooling of tip groove clearance [J]. Journal of Propulsion Technology, 2018, 39(3): 575-582.

虞跨海, 杨茜, 岳珠峰. 高压涡轮冷却叶片叶顶结构气动与传热 [J]. 推进技术, 2012, 33(2): 174-178.

YU Kuahai, YANG Xi, YUE Zhufeng. Aerodynamic and heat transfer of cooling blade tips for high pressure turbine [J]. Journal of Propulsion Technology, 2012, 33(2): 174-178.

刘越奇, 陈绍文, 杨鹏骋, 等. 基于跨声速高压涡轮凹槽叶顶间隙模型的大涡模拟研究 [J]. 推进技术, 2022, 43(5): 110-118.

LIU Yueqi, CHEN Shaowen, YANG Pengcheng, et al. Large eddy simulation on transonic high-pressure turbine cavity tip gap model [J]. Journal of Propulsion Technology, 2022, 43(5): 110-118.

李会, 苏欣荣, 袁新. 基于DDES模拟的叶顶间隙流湍流特性研究 [J]. 工程热物理学报, 2021, 42(2): 342-348.

LI Hui, SU Xinrong, YUAN Xin. Turbulence characteristics of tip leakage flow based on DDES [J]. Journal of Engineering Thermophysics, 2021, 42(2): 342-348.

崔涛, 汪帅, 张伟, 等. 开口双肋凹槽式涡轮叶顶间隙流动数值研究 [J]. 推进技术, 2017, 38(4): 815-827.

CUI Tao, WANG Shuai, ZHANG Wei, et al. Numerical investigation of opening double squealer groove turbine tip clearance flow character [J]. Journal of Propulsion Technology, 2017, 38(4): 815-827.

李鹏, 张超, 刘建军. 燃气透平动叶不同叶顶结构对顶部泄漏流动和换热的影响 [J]. 热能动力工程, 2012, 27(5): 535-539.

LI Peng, ZHANG Chao, LIU Jianjun. Influence of various rotating blade tip structures on the blade tip leakage flow and heat exchange of a gas turbine [J]. Journal of Engineering for Thermal Energy and Power, 2012, 27(5): 535-539.

李琛玺, 郭振东, 宋立明, 等. 凹槽状叶顶气膜孔优化设计与知识挖掘 [J]. 推进技术, 2019, 40(2): 276-284.

LI Chenxi, GUO Zhendong, SONG Liming, et al. Film-cooling holes design optimization and knowledge mining of a squealer tip [J]. Journal of Propulsion Technology, 2019, 40(2): 276-284.

LEE W S, KIM D H, PARK J S, et al. Effect of triangular grooved tip on blade tip region heat transfer [J]. Journal of Thermophysics and Heat Transfer, 2014, 28(2): 226-235.

ZHOU Kai, ZHOU Chao. Aerodynamic effects of an incoming vortex on turbines with different tip geometries [J]. Journal of Turbomachinery, 2021, 143(8): 081009.

FU Yunfeng, CHEN Fu, LIU Huaping, et al. Experimental and numerical study of honeycomb tip on suppressing tip leakage flow in turbine cascade [J]. Journal of Turbomachinery, 2018, 140(6): 061006.

ZHANG Bolun, ZHU Huiren, YAO Chunyi, et al. Investigation on aerothermal performance of a rib-slot scheme on the multi-cavity tip of a gas turbine blade [J]. International Journal of Heat and Mass Transfer, 2021, 176: 121408.

LI Feng, LIU Zhao, FENG Zhenping. Film cooling and aerodynamic performance on multi-cavity squealer tip of a turbine blade [C]//ASME Turbo Expo 2021: Turbomachinery Technical Conference and Exposition. New York, USA: ASME, 2021: V05AT12A025.

LI Feng, JIA Zhe, ZHANG Weixin, et al. Experimental comparisons of film cooling performance for the multi-cavity tips at two different tip gaps [J]. International Journal of Heatand Mass Transfer, 2022, 187: 122566.

杜昆, 李华容, 王力泉, 等. 多腔室凹槽对涡轮叶顶流动传热特性影响的数值研究 [J]. 推进技术, 2022, 43(10): 313-321.

DU Kun, LI Huarong, WANG Liquan, et al. Numerical investigations of multi-cavity tip effects on turbine blade tip flow and heat transfer characteristics [J]. Journal of Propulsion Technology, 2022, 43(10): 313-321.

姜世杰, 李志刚, 李军. 肋条布局对涡轮动叶凹槽状叶顶传热和气动性能的影响研究 [J]. 推进技术, 2020, 41(5): 1103-1111.

JIANG Shijie, LI Zhigang, LI Jun. Effects of rib layout on heat transfer and aerodynamic performance of turbine rotor blade squealer tip [J]. Journal of Propulsion Technology, 2020, 41(5): 1103-1111.

李冯, 贾哲, 张韦馨, 等. 透平动叶多凹槽叶顶气膜冷却特性的研究 [J]. 西安交通大学学报, 2022, 56(8): 149-159.

LI Feng, JIA Zhe, ZHANG Weixin, et al. Study on the film cooling characteristics of multi-cavity turbine blade Tips [J]. Journal of Xi'an Jiaotong University, 2022, 56(8): 149-159.

MOFFAT R J. Describing the uncertainties in experimental results [J]. Experimental Thermal and Fluid Science, 1988, 1(1): 3-17.

浏览量

下载量

CSCD

文章被引用时，请邮件提醒。

提交

工具集

关联资源

隔板位置对凹槽叶顶传热和冷却性能的影响

透平级带压力侧小翼凹槽叶顶的传热与气膜冷却性能研究

压力侧冷却流对凹槽叶顶气膜冷却与传热性能的影响

透平动叶多凹槽叶顶气膜冷却特性的研究

张角凹坑气膜孔对双层壁气膜冷却特性的影响