超声测温技术在模拟航空发动机燃烧室温度测量中的应用  

Ultrasonic Temperature Measurement Technology for Simulated Aero-Engine Combustion Chambers

作　　者：许琳 王高[1] 吕国义[2] 蔡静[2] 杨永军[2] 王晓良 曾行昌 王仲杰[4] XU Lin;WANG Gao;L Guoyi;CAI Jing;YANG Yongjun;WANG Xiaoliang;ZENG Xingchang;WANG Zhongjie(College of Information and Communication, North University of China, Taiyuan 030051, China;Changcheng Institute of Metrology and Measurement, Beijing 100095, China;AVIC Shenyang Engine Design Institute, Shenyang 110015, China;Chinese Flight Test Establishment, Xi’an 710089, China)

机构地区：[1]中北大学信息与通信工程学院,山西太原030051 [2]北京长城计量测试技术研究所,北京100095 [3]中国航发沈阳发动机研究所,辽宁沈阳110015 [4]中国飞行试验研究院,陕西西安710089

出　　处：《测试技术学报》2019年第2期178-184,共7页Journal of Test and Measurement Technology

摘　　要：温度的测试对航空发动机的发展具有重要的意义,燃烧室出口温度是航空发动机的一个重要参数.超声测温技术具有测温范围广、响应快、精度高等优点,近年来被广泛应用于高温测量领域.设计了一套应用于模拟航空发动机燃烧室的超声测温系统.介绍了超声测温的基本原理,设计了基于铱铑合金的超声测温传感器,并在1 600℃高温炉内进行温度与声速的标定实验,最后将铱铑合金超声测温系统应用于模拟航空发动机燃烧室出口气流温度的测量试验中,获得温度-时间曲线,同时将测量结果与热电偶测量数据进行对比分析.结果表明,铱铑超声温度传感器的测量准确度可以达到97%.Combustion chamber outlet temperature measurement is a crucial aspect of the study of modern aero-engines. Ultrasonic temperature measurement technology has a wide temperature range, rapid response capability, and high precision;it has been widely used in high-temperature measurement systems in recent years. A novel ultrasonic temperature measurement system for simulated aero-engine combustion chambers is presented in this paper.The basic principle of ultrasonic temperature measurement is introduced, an ultrasonic temperature sensor based on iridium-rhodium alloy is proposed, and calibration experiments of temperature and ultrasonic velocity conducted in a 1 600 ℃ high-temperature furnace are reported. The ultrasonic temperature measurement system is subjected to an airflow temperature measurement test in the simulated aero-engine combustion chamber to obtain a temperature-time curve, and the measurement results are compared against thermocouple measurement data.

关 键 词：航空发动机燃烧室 出口温度 超声测温 铱铑合金 超声换能器 

分 类 号：TH811[机械工程—仪器科学与技术]