航空发动机进气总温传感器测温误差研究

Research on Temperature Measurement Error of Aero-Engine Inlet Total Temperature Sensor

航空发动机进口总温测量的准确性是优化发动机控制率、保障发动机飞行安全的关键因素之一。针对影响传感器测量准确性的响应时间、恢复系数,通过空气动力学和热力学理论,分析出具体的影响因素,设计了多种结构模型,并通过热风洞试验、FloEFD软件建模和热流体仿真,从材料及结构上系统地提出了优化途径和改善办法并进行了验证,尤其是分析了双余度传感器的响应一致性误差并提出改善方法。研究结果为同类传感器的设计提供了参考和借鉴。

The accuracy of the aero-engine inlet total temperature measurement is one of the key factors to optimize the control rate and ensure the flight safety of the aero-engine. For the response time and recovery factor that affect the measurement accuracy of the sensor,through the aerodynamics and thermodynamics,several structure models were designed and the specific influencing factors were analyzed. Meanwhile,through the thermal wind tunnel test,Flo EFD modeling and thermal fluid simulation,the optimization approach and improvement method were systematically proposed and verified from the material and structure. In particular,the response time consistency error of the dual redundancy sensor was analyzed and its improvement method was proposed. The results provide a reference for the design of similar sensors.