涡轮叶片前缘泄流孔抽吸对回流式冲击流动和换热特性的影响  

Effect of Bleed Hole Extraction on the Flow and Heat Transfer Characteristics in Return-flow Impingement at Turbine Blade Leading Edge

作　　者：王瑞 闫晗 曹子睿 罗磊[2] WANG Rui;YAN Han;CAO Zirui;LUO Lei(AECC Hunan Aviation Powerplant Research Institute,Zhuzhou,China 412002;School of Energy Science and Engineering,Harbin Institute of Technology,Harbin,China 150001)

机构地区：[1]中国航发湖南动力机械研究所,湖南株洲412002 [2]哈尔滨工业大学能源科学与工程学院,黑龙江哈尔滨150001

出　　处：《热能动力工程》2024年第7期11-18,共8页Journal of Engineering for Thermal Energy and Power

基　　金：国家资助博士后研究人员计划(GZC20233441)。

摘　　要：面对涡轮入口温度不断提升造成的日益增长的冷却需要,针对涡轮叶片前缘,提出了一种抑制积聚横流对射流冷却消极影响的回流式冲击冷却结构。采用CFD数值计算方法,通过对多种泄流孔排布形式的数值计算结果进行对比与分析,探究基于此回流式冷却结构下泄流孔的抽吸作用对冷却结构流动和换热特性的影响。结果表明:泄流孔的加入重构了射流冲击流场,一定程度上抑制了壁面射流的发展,降低了冲击靶面的换热强度;相较于3排泄流孔的布置形式,双排泄流孔对靶面换热水平影响更小;相比于泄流孔与冲击孔在流向位置错列排布,二者位置保持一致时,泄流孔的抽吸作用对换热效果削弱最为严重。Facing the increasing cooling requirements caused by the continuously rising inlet temperature of turbines,this paper proposed a return-flow impingement cooling structure to suppress the negative impact of crossflow accumulation on jet cooling at the leading edge of turbine blades.Through the utilization of CFD numerical calculations,a comparative analysis was conducted on the numerical results of various layouts of bleed holes to explore the effects of the suction action of bleed holes on the flow and heat trans-fer characteristics of the cooling structure based on the return-flow impingement cooling structure.The research findings indicate that the introduction of bleed holes reconstructs the impinging jet flow field,effectively restraining the development of wall jets and reducing the heat transfer intensity on the impingement target surface.Compared with the layout with three rows of bleed holes,the layout with two rows of bleed holes has a smaller influence on the heat transfer level on the target surface.Additionally,when the bleed holes and impingement holes are aligned in the same position rather than staggered in the streamwise direction,the suction effect of the bleed holes exhibits the most pronounced weakening effect on the heat transfer performance.

关 键 词：涡轮叶片 回流式冲击冷却 泄流孔 流动与换热 

分 类 号：V232.4[航空宇航科学与技术—航空宇航推进理论与工程]