重燃透平叶片真实内部冷却通道的传热特性研究  

Heat Transfer Characteristics on Realistic Internal Cooling Passages of a Heavy Gas Turbine Blade

作　　者：李立言 李将 张科[1] 雷蒋[1] Li-yan Li;Jiang Li;Ke Zhang;Jiang Lei(State Key Laboratory for Strength and Vibration of Mechanical Structures,Xi’an Jiaotong University)

机构地区：[1]西安交通大学机械结构强度与振动国家重点实验室

出　　处：《风机技术》2022年第6期33-39,共7页Chinese Journal of Turbomachinery

基　　金：国家自然科学基金项目“典型工况下航空燃气轮机涡轮动叶内部冷却弯道的流动传热机理研究”(51776153)。

摘　　要：本文针对重燃叶片真实冷却通道开展传热特性研究。实验模型由前缘、中弦、尾缘三部分通道组成。前缘通道为类三角形截面带肋直通道;中弦通道为带肋蛇形通道;尾缘通道为带肋蛇形通道和相连的柱肋区域。实验在进口雷诺数为30000,40000,50000下进行,利用瞬态液晶测量技术获得通道表面的详细传热分布。结果表明:通道压力面与吸力面的结构差异使三通道的压力面的传热效果均强于吸力面;前缘通道气膜孔出流,导致通道末段传热降低明显;上游冷却单元的流动与下游冷却单元的传热关联性较高,尾缘通道第三通道横向二次流剧烈的区域,其相邻柱肋区域的传热也较高。The present study focuses on the heat transfer characteristics of the realistic cooling passages of a heavy gas turbine blade.The experimental model consists of leading-edge passage,middle-chord passage and trailing-edge passage.The leading-edge passage is a ribbed straight channel with triangular section.The middle-chord passage is a ribbed serpentine channel.The trailing-edge passage consists of a ribbed serpentine channel and a pin-fin region with connection.The tests are conducted at inlet Reynolds number of 30000,40000 and 50000.Transient liquid crystal technique is applied to obtain the detailed heat transfer coefficient distribution on the surface of passages.The results show that the heat transfer of the pressure surface is higher than suction surface because of the structural difference between surfaces.The outflow from the film hole of the leading-edge passage leads to a significant decrease in heat transfer at the end of the channel.The heat transfer distribution in the rib region has a high correlation with upstream flow.The pin-fin area with high heat transfer is adjacent to the area trailing-edge passage where the secondary flow is intense.

关 键 词：重型燃气轮机 真实冷却通道 真实出流 传热特性 

分 类 号：TK474.811[动力工程及工程热物理—动力机械及工程]