航空发动机涡轮燃气出口温度测量系统的研究  

Research on the Mesurement System of Aeroengine Turbine Outlet Temperature

作　　者：杨天南 杨梦迪[2] 

机构地区：[1]海军驻沈阳地区发动机专业军代表室,沈阳110043 [2]中航工业沈阳黎明航空发动机(集团)有限责任公司,沈阳110043

出　　处：《价值工程》2014年第18期38-39,共2页Value Engineering

摘　　要：本文基于航空发动机涡轮燃气出口温度高、要求准确度高的特点,设计了基于热电偶的测温系统,主要应用C8051F340单片机作为核心处理器,热电偶以及补偿电路的电势经过外围放大电路处理后送至高精度24位AD转换芯片AD7714中,AD7714将转换后的数字信号传给单片机,根据热电偶分度表采用查表法得到温度值,由数码管显示,实验验证了这种温度测量系统具有很高的准确度,误差小,电路简单,实用性强。As aeroengine turbine gas outlet temperature is high and has characteristics of high accuracy, the system based on thermocouple is proposed. The system mainly used C8051F340 microcontroller as the core processor. The potential of thermocouple and compensation circuit is sent to high-precision 24-bit AD converter chip AD7714 after being processed by peripheral amplifier circuit. The AD7714 sent the digital signal to the microcontroller and then the microcontroller obtained temperature values from the thermocouple references tables using table look-up method. The nixie tube displayed the result. The experiments verify this temperature measurement system has a very high accuracy, small errors and the circuit is simple and practical.

关 键 词：涡轮燃气出口温度 C8051F340 热电偶 补偿电路 AD7714 

分 类 号：V23[航空宇航科学与技术—航空宇航推进理论与工程]