针对某航空发动机上选用的滑油温度传感器响应速度慢、稳态测温偏差大的问题，以测温偏差的产生机理为导入，通过对测温偏差和时间常数计算公式的推导，明确稳态和动态测温偏差共同的影响因素，并以此为基础，结合滑油温度传感器在发动机上的工作环境和其自身的结构尺寸限制，提出一种增加测温端长径比、提高表面传热系数的传感器测温端结构优化措施。改进后的滑油温度传感器随发动机开展整机试验验证，试验结果表明，改进措施合理有效，改进后的传感器动态响应速度可提升至原传感器的6倍，稳态测温偏差优于1%，能够满足发动机的使用需求。
For the problem of slow response speed and large deviation of steady-state temperature measurement of the lubricating oil temperature sensor selected on a certain type of aeroengine,the generation mechanism of temperature measurement deviation is taken as the import.Through the derivation of the calculation formula of temperature measurement deviation and time constant,the common influence factors of steady-state and dynamic temperature measurement deviation are clarified,and on this basis,combined with the working environment of the lubricating oil temperature sensor on the engine and its own structural size limitations,a structural optimization measure which increasing the length ratio of the temperature measurement end and improving the surface heat transfer coefficient is proposed.The improved lubricating oil temperature sensor follows the engine to carry out the whole machine test and verification,and the test results show that the improvement measures are reasonable and effective,and the improved sensor dynamic response speed can be increased to 6 times that of the original sensor,and the steady-state temperature measurement deviation is better than 1%,which can meet the use demand of the engine.
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