涡轮叶片前腔冲击/气膜复合冷却与单一气膜冷却结构对比实验研究  

Experimental investigation on comparison of impingement/film cooling and pure film cooling structure for a turbine vane leading cavity

作　　者：丁俣中 程想 万红牛 冀文涛 陶文铨 DING Yuzhong;CHENG Xiang;WAN Hongniu;JI Wentao;TAO Wenquan(Key Laboratory of Thermo-Fluid Science and Engineering of MOE,School of Energy and Power Engineering,Xi’an Jiaotong University,Xi’an 710049,China)

机构地区：[1]西安交通大学能源与动力工程学院热流科学与工程教育部重点实验室,陕西西安710049

出　　处：《推进技术》2024年第11期143-151,共9页Journal of Propulsion Technology

基　　金：国家科技重大专项(J2019-Ⅲ-0007-0050)。

摘　　要：为了对比前腔冲击/气膜复合冷却结构和单一气膜冷却结构对涡轮叶片冷却特性的影响,本文以完整叶片为测试对象,针对低导热系数叶片进行了内外耦合综合冷却换热实验。测试叶片前腔压力面采用单一气膜冷却和冲击/气膜复合冷却结构。实验采用红外热像仪测量了叶片表面的温度分布,分析了吹风比(M)对于叶片综合冷却效率的影响。研究了不同工况下两种冷却结构对涡轮叶片冷却特性的影响。实验结果表明,由于叶片表面压力分布不均匀,更靠近前缘的第一排气膜孔处冷却效率小于第二排,且吹风比越小该现象越明显。相较于传统的气膜冷却叶片,冲击/气膜复合冷却叶片在M=0.4,1.2,2.0的情况下,冷却效率分别提升了3.45%,6.33%,5.64%。同时,冲击冷却造成的冷却剂动能损失能够削弱高吹风比下冷却剂出流后脱离壁面的情况发生。In order to compare the flow and heat transfer characteristics of the impingement/film and pure film cooling structure for the turbine vane,a comprehensive conjugate heat transfer experiment was carried out for the complete vane with low thermal conductivity material.The film cooling and impingement/film cooling struc⁃tures were used to the pressure surface of the test vanes leading cavity respectively.In the experiment,the tem⁃perature distribution on the surface of the vane was measured with an infrared thermal imager,and the effects of the blowing ratio(M)on the integrated cooling efficiency were analyzed.The effects of two cooling structures on the cooling efficiency of turbine vanes under different experimental conditions were studied.The results show that due to the uneven pressure distribution on the vane surface,the cooling efficiency of the first film hole closer to the leading edge is lower than that of the second row,and the smaller the blowing ratio is,the more obvious this phenomenon will be.Compared with the traditional film cooling vane,the cooling efficiency of the impingement/film cooling vane increased by 3.45%,6.33%,and 5.64%under the conditions of M=0.4,1.2,and 2.0,respec⁃tively.At the same time,the kinetic energy loss of the coolant caused by impingement cooling can weaken the phenomenon that the coolant detaches from the vane wall after flowing out at a high blowing ratio.

关 键 词：涡轮叶片 气膜冷却 冲击冷却 耦合传热 红外热像仪 

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]