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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 establish the mathematical model of the aeroengine high temperature airflow temperature sensor and give its typical recommended structure, the high temperature airflow temperature sensor is calibrated on the thermal calibration wind tunnel, and the temperature deviation of different temperature sensors under different working conditions is obtained. The influence mechanism of the shield length-diameter ratio, the amount of cooling medium, the wire material, the structure of the sensor, the cooling mode of the housing and the dip angle of the wire are analyzed and the influence law of the temperature deviation of the temperature sensor is obtained. The results show that the temperature deviation of the temperature sensor can be reduced by adopting large aspect ratio, single shielding, dry burning structure, increasing the dip angle of the coupling wire, adopting the even wire material with low thermal conductivity, and reducing the cooling medium amount When the aspect ratio is ≥5, the relative temperature deviation of the temperature sensor below 1300 ℃ does not exceed 2.2%.