异型扰流-狭缝气膜层板结构的冷却特性分析  

Analysis of Cooling Characteristics of lrregular Turbulent Flow-slit Gas Film Laminate Structure

作　　者：张强[1] 吉洪湖[1] 梁萌 朱强华 ZHANG Qiang;JI Honghu;LIANG Meng;ZHU Qianghua(College of Energy and Power,Nanjing University of Aeronautics and Astronautics,Nanjing 210016,China;Nanchang Hangkong University,Nanchang 330063,China)

机构地区：[1]南京航空航天大学能源与动力学院,江苏南京210016 [2]南昌航空大学,江西南昌330063

出　　处：《机械制造与自动化》2022年第4期44-47,共4页Machine Building & Automation

摘　　要：针对航空发动机涡轮导向叶片前缘的结构设计,研究一种异型扰流与狭缝气膜冷却相结合的层板结构,采用正交试验设计方法设计9种冷却结构模型。分析扰流柱形状、扰流柱尺寸与其布置方式、进气口直径、狭缝出口倾斜角等参数对这种新型结构冷却效果的影响,得到各模型的流动传热规律并进行对比分析。分析结果表明:各模型冷却效果接近,第三套模型总压损失系数最小为0.26,壁温最低、换热强度较大且平均冷却效率最高。A new type of laminar structure with special-shaped turbulence and slit film cooling is studied for designing the structure of the leading edge of aero-engine turbine guide vane.Nine cooling structure models are designed by orthogonal test design method.The analysis on the impacts of the shape,size and arrangement of the spoiler,the diameter of the inlet and the inclination angle of the slot outlet on the cooling effect of the new structure is conducted to obtain and compare the flow and heat transfer laws of each model.The analysis results show that cooling effect of each model is similar,and the third model has the lowest total pressure loss coefficient of 0.26 with the lowest wall temperature,higher heat transfer intensity and the highest average cooling efficiency.

关 键 词：涡轮叶片 流动传热 层板冷却 狭缝气膜 异型扰流 

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]