航空发动机矢量喷管位移传感器冷却研究

Displacement Sensor Cooling of Aero Engine Vectoring Nozzle

关键词:  航空发动机  矢量喷管  位移传感器  冷却  热分析

Key words:  Aero engine  Vectoring nozzle  Displacement sensor  Cooling  Heat analysis

摘要:

为了降低典型航空发动机矢量喷管作动器中位移传感器的工作温度，提出了一种传感器主动冷却结构，基于真实工况条件建立了传感器热分析计算模型，编制了FORTRAN程序进行了求解，搭建了试验台对计算结果准确性进行验证，探究了工况参数变化对传感器温度的影响。结果表明，本文编制的传感器热分析程序计算结果具有准确性，主动冷却结构对传感器的冷却效果明显。活塞杆位置对传感器温度随工况参数变化规律具有明显的影响。冷却介质入口温度对传感器温度影响最大。在活塞杆完全伸出时，冷却介质入口体积流量对传感器温度的影响大于环境温度；活塞杆完全收进时，结果正好相反。

Abstract:

In order to decrease the working temperature of displacement sensor on actuator of typical aero engine vectoring nozzle， an active cooling structure of displacement sensor is presented， the displacement sensor heat analysis model is established based on the real working condition， and the Fortran program is compiled to solve the heat analysis model. A test-bed is built in order to verify the accuracy of the analysis model. The effects of working condition parameters’ variation on sensor temperature are investigated. The results show that the computational result of heat analysis model is accurate. The active cooling structure has significant cooling effects on displacement sensor. The position of piston rob has obvious effects on the variation of displacement sensor temperature caused by the variation of working condition parameters. The variation of cooling medium entrance temperature has the biggest effects on displacement sensor temperature compared with other working condition parameters. When the piston rob reaches out， cooling medium entrance flowing rate has bigger effects on sensor temperature than environment temperature does， and the conclusion is opposite when the piston rob draws in.