一种航空发动机防冰传感器测温特性试验研究

Experimental Study on Temperature Characteristic of an Engine Anti⁃icing Sensor

为了研究热气防冰传感器的测温特性,对一种航空发动机热气防冰传感器开展了冰风洞试验研究,获得了传感器测温特性随来流总温、热气流量、热气温度及水滴参数的变化结果。试验结果表明,热气参数对传感器的测温特性影响较大,随着热气温度和流量的升高,传感器测量偏差度增大;传感器使用环境受航空发动机工作状态的影响,在一定条件内,传感器测量偏差度在合理范围内波动;热气防冰传感器在过冷水滴结冰环境下存在结冰现象,结冰会影响传感器测温腔入口气流,导致传感器测温偏差增大,降低传感器测温性能;当结冰量过多时,传感器失真失效。

The test study on temperature characteristic of an engine anti-icing sensor is carried out in the icing wind tunnel.The results of temperature characteristic changing with air total temperature,heat air flow,heat temperature as well as the droplet parameters are obtained.The experimental results show that the heat air parameters have great effect on the temperature characteristic of the sensor,and the average measuring deviation of the sensor increases as the heat air temperature and flow increase.Sensor application scenario is affected by the aircraft engine operation.In certain conditions,the average measurement deviation of the sensor fluctuates in a reasonable range.The ice formed on the sensor will affect the air flow into the sensor temperature cavity,and cause the increase of the sensor temperature deviation.This will finally lead to the decrease of the sensor performance and even failure of the sensor if the ice amount is too much.