双层壁涡轮叶片短径扇形气膜孔冷却性能数值研究  

Numerical Study on Cooling Performances of Short Fan-shaped Film Holes on a Double-wall Cooled Turbine Vane

作　　者：刘新宇 王建华[1] 浦健 姚然 Xin-yu Liu;Jian-hua Wang;Jian Pu;Ran Yao(Department of Thermal Science and Energy Engineering,University of Science and Technology of China;Institute of Engineering Thermophysics,Chinese Academy of Sciences)

机构地区：[1]中国科学技术大学工程科学学院 [2]中国科学院工程热物理研究所

出　　处：《风机技术》2024年第3期1-7,共7页Chinese Journal of Turbomachinery

基　　金：国家科技电大专项(J2019-I-0008-0028)。

摘　　要：针对高冷效双层壁涡轮叶片表面应用短径扇形孔设计准则及强化气膜冷却,机理依旧不明的现状,本文利用流固弱耦合数值模拟技术研究了典型7-7-7和11-11-11扇形气膜孔应用于双层壁涡轮叶片设计的冷却特性。在宽范围吹风比下(0.6~2.4),比较了三种扇形气膜孔布置方案,包含叶片两侧同构布局7-7-7孔(简称SH1布局)和11-11-11孔(简称SH2布局)及新提出的异构布局(简称SH3布局),并以常规圆形孔作为比较依据。通过数值结果对比指出:在双层壁表面应用扇形孔代替圆形孔,最低可提升吸力面综合冷却效率17%,压力面7%。然而,扇形孔也会诱导两侧冷却性能差异扩大的现象。应用两侧孔型异构布局,要求在压力侧布置相较于吸力侧各向扩张角更大的扇形孔,可以有效改善叶片内部的流量配置,从而在提升综合冷却效率的基础上兼顾两侧温差缩小。在高吹风比条件下,上述异构诱发的冷却优势更为显著。但相对吸力侧、压力侧对扇形孔型结构参数的敏感性更大。因此,压力侧的异型孔气膜冷却挑战性更大。To capture the cooling mechanisms of fan-shaped film-holes at the surface of advanced doble-wall cooled vanes,a conjugate heat transfer numerical simulation was conducted to examine the cooling characteristics of typical 7-7-7 and 11-11-11 fan-shaped film cooling holes on the double-wall turbine vane.Under a large range of blowing ratios from 0.6 to 2.4,three distinct fan-shaped film hole arrangements were compared,including:1)SH1 layout where both the suction and pressure sides were equipped with 7-7-7 fan-shaped holes;2)SH2 layout where both sides featured 11-11-11 fan-shaped holes;and 3)proposed SH3 layout where the suction side was equipped with 7-7-7 holes while the pressure side had 11-11-11 holes.In addition,the cylindrical-hole was chosen as the reference.The comparisons of numerical results revealed that relative to the cylindrical-hole layout,the designs of fan-shaped-hole can improve the overall effectiveness by 17%at suction side and 7%at pressure side at least,respectively.However,the designs of fan-shaped-hole can induce the larger thermal gradient over two sides of vane.Application of SH3 can displayed the smallest discrepancy in cooling effectiveness between the suction and pressure sides among three types of fan-shaped-hole-configurations,due to the more proper outflow allocation.The benefit of SH3 can be enlarged under the larger blowing ratio.In comparison with the cooling at suction side,the cooling effectiveness at pressure side is more sensitive to the configuration of film-hole,bringing to the larger challenge for the cooling optimization.

关 键 词：双层壁冷却叶片 短径扇形孔 气膜冷却 异构布局 流固耦合传热 

分 类 号：V231.1[航空宇航科学与技术—航空宇航推进理论与工程] TK12[动力工程及工程热物理—工程热物理]