高温气流温度传感器测温偏差关键影响因素分析  

Analysis of Key Influencing Factors on Temperature Measuring Deviation of High Temperature Gas Sensors

作　　者：赵俭[1] 荆卓寅[1] 李亚晋 

机构地区：[1]中航工业北京长城计量测试技术研究所,北京100095

出　　处：《航空发动机》2017年第3期78-82,共5页Aeroengine

摘　　要：为建立航空发动机高温气流温度传感器的数学模型,并给出其典型推荐结构,对高温气流温度传感器在热校准风洞上进行校准,得到不同温度传感器在不同工况条件下的测温偏差,并针对屏蔽罩长径比、冷却介质量、偶丝材料、传感器结构、外壳冷却方式以及偶丝倾角等关键影响因素,对其影响机理进行分析,得到了温度传感器测温偏差的影响规律。结果表明,采用大长径比、单屏蔽、干烧式结构,增大偶丝倾角,采用低导热系数的偶丝材料、以及减少冷却介质量,均可减小温度传感器的测温偏差,当长径比≥5时,温度传感器在1300℃以下的相对测温偏差不超过2.2%。In order to build mathematical model and provide typical recommended structure of high temperature gas sensors in aeroengine, temperature measuring deviations of different temperature sensors under different conditions were obtained by calibration in the hot wind tunnel. Aiming at the key influencing factors, including length-diameter ratio of shield, flow of cooling-medium, material of thermal couple wire, structure of temperature sensor, cooling method of shell and angle of thermal couple wire, influencing mechanism was analyzed, and influence laws were obtained. Results show that adoption of greater length-diameter ratio structure, single shield structure, no cooling structure, low thermal conductivity materials of thermal couple wire and less amount of cooling medium can all decrease temperature measuring deviations of sensors. Relative temperature measuring deviation below 1300 ℃ will be no more than 2.2% when length-diameter ratio is no less than 5.

关 键 词：温度传感器 高温气流 测温偏差 影响因素 航空发动机 

分 类 号：V241.75[航空宇航科学与技术—飞行器设计]