液体火箭发动机燃烧室壁温与火焰温度分布红外感应测量技术  

Temperature measuring technologies of rocket combustor by an infrared camera

作　　者：洪流[1] 仲伟聪[2] 王玫[2] 

机构地区：[1]西北工业大学动力与能源学院,陕西西安710072 [2]西安航天动力研究所,陕西西安710100

出　　处：《火箭推进》2007年第4期47-51,共5页Journal of Rocket Propulsion

摘　　要：在实验室条件下,采用热电偶和红外测温仪同时对不锈钢和带辐射涂层的铌合金表面的温度及燃气温度进行测量,应用温度测量值来修正材料表面的黑度值及燃气的黑度值,利用黑度测量结果对某发动机试车时的温度场进行了测量,并与燃气的理论计算黑度值进行了对比。试验结果表明,这种方法对铌合金材料的壁温测量结果比较准确,而对不锈钢材料壁温测量结果准确度不是很理想。红外测温技术对燃气的温度测量结果与计算结果比较接近。To obtain the temperature of a material accurately by an infrared camera, it is important to set a right blackness of the material. In the present paper thermocouples and an infrared camera were used to measure the temperature on the surface of a stainless steel plate and a niobic alloy plate and the temperature of hot gas. With the temperature measured in two different ways, the blackness of the solid materials and hot gas can be corrected. The temperature measuring results for hot test of an engine with the corrected blackness show that wall temperatures and gaseous temperatures of the engine measured by infrared camera and the thermocouples are similar.

关 键 词：红外测温 黑度 铌合金 不锈钢 燃气 

分 类 号：V434[航空宇航科学与技术—航空宇航推进理论与工程]