涡轮叶片表面热电偶集成结构设计与影响因素分析  

Analysis on Turbine Blade Surface Thermocouple Integration Structure Design and Influencing Factor

作　　者：牛宏伟[1] 董江 王烨 Niu Hongwei;Dong Jiang;Wang Ye(Chinese Flight Test Establishment,Xi’an 710089,China)

机构地区：[1]中国飞行试验研究院,陕西西安710089

出　　处：《航空科学技术》2023年第2期96-103,共8页Aeronautical Science & Technology

基　　金：航空科学基金(2019ZD030006)。

摘　　要：航空发动机涡轮转子叶片工作在高温、高转速、高气动负荷的极端恶劣环境下,在进行表面温度测量时,热电偶在叶片表面的集成/防护尤为重要,热电偶集成结构各组件之间的结合强度决定了涡轮转子及附加测量结构能否安全稳定运行。本文针对基于增材制造和火焰喷涂的涡轮叶片表面热电偶集成结构,以涂层厚度、热电偶直径及增材结构形式作为设计参数,共设计9种热电偶集成结构,进行有限元仿真和强度分析,研究各变量对组件结合面强度的影响。根据分析结果,从参数矩阵中选择最优的设计构型,进行热电偶集成/防护,并通过高速旋转试验验证了其应用潜力。The turbine rotor blade of aero-engine works in the extremely harsh environment of high temperature,high speed and high aerodynamic loadings.When measuring the surface temperature,the integration/protection of thermocouples on the blade surface is particularly important.The combination strength between the components of the thermocouple integration structure determines whether the turbine rotor and the additional measurement structure can operate safely and stably.In this paper,nine kinds of thermocouple integration structures are designed for the turbine blade surface thermocouple integration structure based on additive manufacturing and flame spraying,which takes the coating thickness,thermocouple diameter and additive structure form as the design parameters.The finite element simulation and strength analysis are carried out to study the influence of various variables on the strength of the component interface.According to the analysis results,the optimal design configuration is selected from the parameter matrix for thermocouple integration/protection,and its application potential is verified by high-speed rotation test.

关 键 词：涡轮叶片 热电偶 集成结构 切应力 涂层 增材结构 

分 类 号：V235.13[航空宇航科学与技术—航空宇航推进理论与工程]