摘要
在使用RotamapⅡ红外测试系统前需要已知被测涡轮叶片的表面发射率。阐述了1种使用电涡流加热涡轮叶片,从而获得较大温度范围内的涡轮叶片表面发射率的方法。试验测试了某型航空发动机的新、旧2种高压涡轮叶片的表面发射率。试验结果表明:不同温度下叶片的发射率数值会发生变化,新叶片的表面发射率随温度的升高而明显增大,当叶片表面发生严重氧化后发射率变化较小,在±0.02之间。采用RotamapⅡ系统测试某型发动机高压涡轮叶片温场时,发射率数值可以取0.893,其测温误差小于被测物体温度的1%。同时结合试验得出的发射率造成的测温误差曲线可以对红外测温结果进行修正。
It is necessary to know the surface emissivity of some turbine blades before using the Rotamap II pyrometer system. By using the eddy current heating technology can obtain the surface emissivity in a large temperature range. The new and the old turbine blades were tested in the experiment. The experimental result shows that the emissivity will be changed in different temperatures, and the emissivity of the new turbine blade will be increased with the rising of temperature. Once the blade surface is oxidized, the emissivity variation value is small, and is in the range of i-0.02. In the Rotamap I] pyrometer system, the emissivity value can adopt 0.893, the error that caused by emissivity is less than 1% of the subject temperature. The temperature can be updated using the temperature error caused by emissivity error curve.
出处
《航空发动机》
2015年第2期89-92,共4页
Aeroengine
基金
航空动力基础研究项目资助
关键词
高压涡轮叶片
发射率
温度场
测量
红外测温
电涡流加热
航空发动机
high pressure tubine blades
emissivity
temperature filed
measurement
infrared temperature measurement
eddy current heating
aeroengine
