航空发动机矢量喷管作动器伺服阀非稳态热分析

Transient Heat Transfer Analysis for Servo Valve of Aero Engine Vectoring Nozzle

采用集总参数法,对航空发动机矢量喷管作动器伺服阀进行了非稳态热分析,建立了相应的数学模型,研究了环境温度、伺服阀初始温度和伺服阀焦耳热对伺服阀温度随时间的变化规律。结果表明:伺服阀的稳定温度只随环境温度和伺服阀焦耳热的增大而升高,与伺服阀初始温度无关。伺服阀超温时间随着初始温度、环境温度、伺服阀焦耳热的增大而缩短:环境温度为300℃,伺服阀焦耳热为0.08W时,初始温度从50℃到100℃,超温时间缩短20.6%。伺服阀焦耳热为0.08W,初始温度为70℃,环境温度从250℃上升400℃时,超温时间缩短了60.8%。环境温度为300℃,初始温度为122.6℃时,10W的伺服阀焦耳热相比0.08W,超温时间缩短了38.3%。

The servo valve of aero engine vectoring nozzle is analyzed by the lumped parameter method. The variation of the time dependent temperature of the servo valve under the influence of ambient temperature, the initial temperature and the Joule heat of the servo valve is studied through the establishment of the corresponding mathematical model. The results show that： the steady temperature of servo valve only increases with the increase of ambient temperature and Joule heat, and is independent of the initial temperature of servo valve. The over temperature time of servo valve is shortened with the increase of initial temperature, ambient temperature and Joule heat. When the ambient temperature is 300℃ and the servo valve has a Joule heat of 0.08 W, the initial temperature changes from 50℃ to 100℃, and the over temperature time is shortened by 20.6%. When the Joule heat of servo valve is 0.08 W, the initial temperature is 70℃ and the ambient temperature rises from 250 ℃ to 400℃, the o- ver temperature time is shortened by 60.8℃. When the ambient temperature is 300℃ and the initial temperature is 122.6℃, Joule heat of 10 W compared with that of 0.08 W, the over temperature time is shortened by 38.3%.