热风洞中涡轮叶片温度场红外热像测量方法  

Method of infrared thermography measurement for temperature field of turbine vane in hot wind tunnel

作　　者：黄名海[1] 臧树升[1] 葛冰[1] 翁史烈[1] 

机构地区：[1]上海交通大学机械与动力工程学院,上海200240

出　　处：《航空动力学报》2014年第11期2679-2683,共5页Journal of Aerospace Power

摘　　要：提出了在热风洞中利用红外热像来测量涡轮叶片表面温度场的方法.针对热风洞特有的干扰因素,即石英玻璃窗口的透射比随着叶片表面温度变化以及燃气中的二氧化碳和水蒸气等组分参与热辐射所带来的干扰,在取得红外热像后按照燃气工况对温度场测量结果进行综合修正.考虑到叶片表面曲率的变化,通过几何上的变换重现了实际叶片表面上的温度场.结果表明：在热风洞的叶片温度场的红外热像测量中存在着110~140K的修正量.高温燃气环境中的红外热像测量结果必须按工况进行修正.A method of obtaining the temperature field of the surface of turbine vane in hot wind tunnel utilizing infrared thermography measurement was presented.After the acquirement of infrared thermograms,overall corrections were implemented pertaining to the specific disturbance of hot wind tunnel caused by variations in the transmission rate of quartz glass window with the vane surface temperature,as well as by thermal radiation of gas components such as carbon dioxide and water vapor.A geometrical transformation could help reproducing the temperature field of the vane surface,by taking into consideration the curvature of the vane surface.The results show that corrections as large as 110-140 Kexists for infrared thermography measurement of this testing in hot wind tunnel.Under hot gas circumstances,temperature correction based on gas conditions is indispensable.

关 键 词：热风洞实验 涡轮叶片 红外热像 温度场测量 燃气热辐射 

分 类 号：V211.753[航空宇航科学与技术—航空宇航推进理论与工程]