摘要
采用等离子电弧加热器双模型矩形湍流导管试验技术模拟了发动机内流热环境,对背面喷涂了高辐射涂层的发动机防热材料进行了热防护性能考核.利用改进的试验件安装方法,在防热材料的背面提供了开敞式的常温环境,使防热材料的高温背面能够对周围常温环境辐射散热,模拟了防热材料背面的换热环境.采用K型热电偶和单色红外测温仪测量了防热材料背面高辐射涂层的温度.根据以上两种不同测温方式测量的温度曲线,得到了该背面喷涂的高辐射涂层材料的光谱发射率随温度的变化曲线.试验结果表明：背面喷涂了高辐射涂层的材料背面温度比材料背面没有涂层的低了81.1 K;当温度在1 103～1 153K时,该高辐射涂层材料的光谱发射率ελ（λ=1.6 μm）为0.89 ～0.77,随温度升高,ελ呈下降趋势.
The inner flow thermal environment of engine has been simulated by the arc-heater double-models rectangle turbulent duct technique in this paper. And the thermal protection performance of the thermal protection ma- terials with high-emissivity rear coating has been tested. The improved model installation method, which can provide open-type environment with normal temperature in the material rear, can make sure that the rear coating of material can radiated energy to the atmosphere or wall with normal temperature. And the heat transfer environment of the mate- rial rear has been simulation by this method. The type-K thermocouples and single-wavelength infrared thermometer were used to measure the high-emissivity rear coating temperature. According to the rear temperatures measured by the two kinds of instruments, the spectral emissivity vs. temperature curve can be found. The results show that the rear temperature of thermal protection materials with high-emissivity rear coating is 81.1 K lower than that without high-emissivity rear coating. The spectral emissivity of high-emissivity rear coating ελ（A = 1.6 p.m） is 0.89 to 0.77 for the temperature range from 1 103 to 1 153 K, and sx decreases when the temperature increases.
出处
《宇航材料工艺》
CAS
CSCD
北大核心
2013年第5期65-69,共5页
Aerospace Materials & Technology
关键词
电弧加热器
内流热环境
发动机防热材料
背面高辐射涂层
光谱发射率
Arc heater, Inner flow thermal environment, Engine thermal protection materials, High-emissivityrear coating, Spectral emissivity
