航空涡轮叶片表面红外温度测量  

Infrared Temperature Measurement of Aircraft Turbine Blade Surface

作　　者：张天宇 吴嘉雯 方弘毅 张彪[1] 贺振宗 许传龙[1] ZHANG Tian-yu;WU Jia-wen;FANG Hong-yi;ZHANG Biao;HE Zhen-zong;XU Chuan-long(National Engineering Research Center of Power Generation Control and Safety,School of Energy and Environment,Southeast University,Nanjing 210096,China;AECC Sichuan Gas Turbine Establishment,Mianyang 621000,China;College of Energy and Power Engineering,Nanjing University of Aeronautics and Astronautics,Nanjing 210016,China)

机构地区：[1]东南大学能源与环境学院大型发电装备安全运行与智能测控国家工程研究中心,江苏南京210096 [2]中国航发四川燃气涡轮研究所,四川绵阳621000 [3]南京航空航天大学能源与动力学院,江苏南京210016

出　　处：《节能技术》2023年第3期195-202,223,共9页Energy Conservation Technology

基　　金：国家自然科学基金资助项目(52176167);江苏省自然科学基金资助项目(BK20201279)。

摘　　要：本文针对航空发动机涡轮叶片红外辐射测温方法中因受干扰因素多而导致的测温精度难以保证的问题,通过对曲面表面的发射率、双向反射分布函数、角系数等参数的测量,提出了一种用于三维弯曲表面的测温修正方法。通过实验室实验,并与典型位置上热电偶测温结果对比,测量修正后温度的误差稳定在1%以内,验证了本文所提修正方法的可行性,为涡轮叶片气动传热试验技术的提升和我国航空发动机等重大装备的研制提供支撑。This paper addresses the issue of accuracy in temperature measurement of turbine blades,which is hindered by several interference factors in the method of infrared radiation temperature measurement.To overcome this challenge,a novel approach is proposed in which the emissivity,bidirectional reflection distribution function,and angle coefficient of the curved surface are measured.This approach enables a thermal correction method to be developed for three-dimensional curved surfaces.Laboratory experiments were conducted to validate the proposed method.The corrected temperature measurements were compared against those obtained using thermocouples at typical positions,and the error rate was found to be stable within 1%.This finding confirms the feasibility of the proposed correction method and provides a basis for improving the aerodynamic heat transfer test technology of turbine blades.Moreover,this research provides support for the development of major aero-engine equipment in the country.

关 键 词：航空发动机 辐射测温 测量 发射率 涡轮叶片 

分 类 号：TK311[动力工程及工程热物理—热能工程]