某型发动机低压涡轮盘温度遥测技术

Temperature measurement of low pressure turbine disk based on telemetry technology

涡轮盘作为航空发动机中的一个关键热端部件,是影响发动机特性的一个重要因素,准确获取整机工作中涡轮盘的温度数据,对于发动机研制工作十分重要。该文设计出一种基于遥测技术的测温方法,以完成对某型航空发动机高温、高速旋转以及强振动工况条件下涡轮盘的温度测量。试验前完成电偶的安装和引线,发动机的测试改装,冷却系统的设计,并对遥测系统进行标定,遥测系统测试精度优于±0.6℃,数据真实可信。试验过程中,遥测系统工作正常,测点连续性好、存活率高。试验结果表明,通过“热电偶-遥测系统”的测量方法能有效获取发动机稳态和过渡态低压两级涡轮盘壁温腔温,具有较强的工程应用价值。

As a key hot end component in aeroengine,turbine disk is an important factor that affects engine characteristics.It is very important for engine development to accurately obtain the temperature data of turbine disk during the whole engine operation.In this paper,a temperature measurement method based on telemetering technology is designed to measure the temperature of turbine disk under the conditions of high temperature,high-speed rotation and strong vibration of an aeroengine.Before the test,the installation and lead of the thermocouple,the test and refit of the engine,the design of the cooling system were completed,and the telemetry system was calibrated.The test accuracy of the telemetry system was better than±0.6℃,and the data was authentic.During the test,the telemetry system worked normally,with good continuity of measuring points and high survival rate.The test results show that the measurement method of"thermocouple telemetry system"can effectively obtain the wall temperature cavity temperature of low pressure two-stage turbine disk in steady state and transient state,and has strong engineering application value.