郭嘉杰,梁崇治,郭振东,宋立明,李军

• 1:西安交通大学能源与动力工程学院
• 2:东方汽轮机有限公司电站服务事业部

摘要(Abstract)：

为进一步提高凹槽叶顶的冷却与气动性能，基于Kriging代理模型优化算法，耦合商业CFD分析软件，引入椭圆冷却孔型，设计了凹槽叶顶冷却孔组合偏转角参数化方法，并建立了组合偏转角自动优化框架。以实验条件下的GE-E~3首级动叶的叶顶冷却孔布局为研究对象，兼顾冷却与气动两方面性能，开展了凹槽叶顶的冷却孔优化设计与气热分析。研究结果显示，在凹槽叶顶布置吸力面朝向与凹槽尾缘朝向的组合偏角气膜孔能有效增强气膜的贴壁性能，扩大气膜的覆盖范围，同时引导了射流向凹槽尾缘堆积，提升了刮削涡对泄漏流的阻塞作用，有效降低了泄漏流量。椭圆孔依靠低曲率的长轴边出流，相较于圆形孔进一步扩大了气膜覆盖范围并提升了贴壁性能，使凹槽尾缘的流线堆积效应相应增强，进一步地减少了泄漏流量。圆形孔优化结构相比参考结构的气膜冷却效率提高了331.7%,泄漏流量相对减少了1.641%;椭圆孔优化结构的气膜冷却效率提升了565.1%,泄漏流量相对减少率为2.063%。

关键词(KeyWords)： 气膜冷却;凹槽叶顶;全局优化算法

Abstract:

Keywords:

基金项目(Foundation): 国家科技重大专项资助项目（2019-Ⅱ-0008-0028）;; 国家自然科学基金资助项目（51936008）

作者(Author): 郭嘉杰,梁崇治,郭振东,宋立明,李军

参考文献(References)：

• [1] BUNKER R S.Axial turbine blade tips:function,design,and durability [J].Journal of Propulsion and Power,2006,22(2):271-285.
• [2] MORPHIS G,BINDON J P.The performance of a low speed one and a half stage axial turbine with varying rotor tip clearance and tip gap geometry [C]//ASME 1994 International Gas Turbine and Aeroengine Congress and Exposition.New York,NY,USA:ASME,1994:V001T01A152.
• [3] HOLESKI D E,FUTRAL S M Jr.Effect of rotor tip clearance on the performance of a 5-inch single stage axial flow turbine:19690011521 [R].Washington DC,USA:NASA,1969.
• [4] HAN J C.Fundamental gas turbine heat transfer [J].Journal of Thermal Science and Engineering Applications,2013,5(2):021007.
• [5] DENTON J D.The 1993 IGTI scholar lecture:loss mechanisms in turbomachines [J].Journal of Turbomachinery,1993,115(4):621-656.
• [6] SJOLANDER S A,CAO D.Measurements of the flow in an idealized turbine tip gap [J].Journal of Turbomachinery,1995,117(4):578-584.
• [7] HEYES F J G,HODSON H P.Measurement and prediction of tip clearance flow in linear turbine cascades [J].Journal of Turbomachinery,1993,115(3):376-382.
• [8] KWAK J S,HAN J C.Heat-transfer coefficients of a turbine blade-tip and near-tip regions [J].Journal of Thermophysics and Heat Transfer,2003,17(3):297-303.
• [9] KWAK J S,HAN J C.Heat transfer coefficients and film-cooling effectiveness on a gas turbine blade tip [J].Journal of Heat Transfer,2003,125(3):494-502.
• [10] KRISHNABABU S K,NEWTON P J,DAWES W N,et al.Aerothermal investigations of tip leakage flow in axial flow turbines:part Ⅰ effect of tip geometry and tip clearance gap [J].Journal of Turbomachinery,2009,131(1):011006.
• [11] KEGALJ M,SCHMID G,WARTZEK F,et al.Experimental and numerical investigation of tip leakage flow in a 1 1/2 stage turbine rig comparing flat and cavity-squealer tip geometries [C]//ASME Turbo Expo 2012:Turbine Technical Conference and Exposition.New York,NY,USA:ASME,2012:1543-1557.
• [12] ZHANG D H,ZENG M,WANG Q W.The influence of rotating speed on film cooling characteristics on GE-E3 blade tip with different tip configurations [C]//ASME Turbo Expo 2009:Power for Land,Sea,and Air.New York,NY,USA:ASME,2009:1017-1025.
• [13] NIU Maosheng,ZANG Shusheng.Experimental and numerical investigations of tip injection on tip clearance flow in an axial turbine cascade [J].Experimental Thermal and Fluid Science,2011,35(6):1214-1222.
• [14] ZHOU Chao,HODSON H.The tip leakage flow of an unshrouded high pressure turbine blade with tip cooling [J].Journal of Turbomachinery,2011,133(4):041028.
• [15] VOLINO R J.Control of tip leakage in a high pressure turbine cascade using tip blowing [C]//ASME Turbo Expo 2016:Turbomachinery Technical Conference and Exposition.New York,NY,USA:ASME,2016:V02BT38A019.
• [16] GAO Jie,ZHENG Qun,ZHANG Zhengyi,et al.Aero-thermal performance improvements of unshrouded turbines through management of tip leakage and injection flows [J].Energy,2014,69:648-660.
• [17] ZHOU Zhihua,CHEN Shaowen,LI Weihang,et al.Thermal performance of blade tip and casing coolant injection on a turbine blade with cavity and winglet-cavity tip [J].International Journal of Heat and Mass Transfer,2019,130:585-602.
• [18] 于金杏，叶明亮，何坤，等.压力侧冷却流对凹槽叶顶气膜冷却与传热性能的影响 [J].西安交通大学学报，2022,56(3):160-172.YU Jinxing,YE Mingliang,HE Kun,et al.Effect of Pressure-Side cooling flow on film cooling and heat transfer performance at squealer tip [J].Journal of Xi’an Jiaotong University,2022,56(3):160-172.
• [19] 轩笠铭，邹正平，赵强，等.叶顶喷气对凹槽叶尖气动性能的影响 [J].航空动力学报，2022,37(5):1030-1041.XUAN Liming,ZOU Zhengping,ZHAO Qiang,et al.Effect of tip injection on aerodynamic performance of squealer tip [J].Journal of Aerospace Power,2022,37(5):1030-1041.
• [20] 许承天，李志刚，李军.考虑气膜冷却脉动特性的涡轮动叶凹槽状叶顶气动和冷却性能研究 [J].西安交通大学学报，2022,56(5):127-140.XU Chengtian,LI Zhigang,LI Jun.Study on aerodynamic and cooling performance of turbine blade squealer tip with film cooling pulsation characteristics considered [J].Journal of Xi’an Jiaotong University,2022,56(5):127-140.
• [21] KANG Y S,RHEE D H,KIM C T,et al.Aerodynamic optimization of axial turbine tip cavity with approximation model [C]//ASME 2013 Turbine Blade Tip Symposium.New York,NY,USA:ASME,2013:V001T01A005.
• [22] 金家辉，宋彦萍，俞建阳，等.基于样条曲面及代理模型的涡轮叶顶修型研究 [J].工程热物理学报，2019,40(1):49-54.JIN Jiahui,SONG Yanping,YU Jianyang,et al.Modification for turbine blade tips on b-spline surface and kriging model [J].Journal of Engineering Thermophysics,2019,40(1):49-54.
• [23] 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.
• [24] 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.
• [25] KWAK J S,AHN J,HAN J C,et al.Heat transfer coefficients on the squealer tip and near-tip regions of a gas turbine blade with single or double squealer [J].Journal of Turbomachinery,2003,125(4):778-787.