CAJ | 학술논문

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。
본문기우항공발동궤와륜연기출구온도고、요구준학도고적특점，설계료기우열전우적측온계통，주요응용C8051F340단편궤작위핵심처리기，열전우이급보상전로적전세경과외위방대전로처리후송지고정도24위AD전환심편AD7714중，AD7714장전환후적수자신호전급단편궤，근거열전우분도표채용사표법득도온도치，유수마관현시，실험험증료저충온도측량계통구유흔고적준학도，오차소，전로간단，실용성강。
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.