应用积分法的发动机内壁瞬态温度测试研究  

Study of integration in measuring inside-wall surface transient temperatures of aero-engine

作　　者：郭海伟[1] 郝晓剑[1] 周汉昌[1] 潘保武[1] 

机构地区：[1]中北大学仪器科学与动态测试教育部重点实验室

出　　处：《电子测试》2011年第10期1-4,74,共5页Electronic Test

基　　金：山西省电子测试技术重点实验室基金项目资助(9140C1204040705)

摘　　要：在传热学基本原理和能量守恒定律的基础上,本文提出了利用积分法求解航空发动机壁面导热的偏微分方程,进而实现对航空发动机内壁瞬态温度的测量。借助螺塞热电偶温度传感器和多路数据采集卡,建立了瞬态温度测量系统,利用氢氧焰模拟航空发动机内部瞬态高温源,分别得出了传感器和红外测温仪测得的发动机内壁表面温度变化曲线。实验结果表明该方法可行。与传统的分析法相比,该方法解的形式简单,测量精确度较高,便于工程上的应用。This paper presents integration method to solve thermal conduction differential equation based on the fundamental principles of heat transfer and law of conservation of energy in order to measure inside-wall surface temperatures of aero-engine. Transient high temperature testing system was established by Oxy-hydrogen flame simulating the transient high-temperature heat source within the aero-engine, with the help of screw thermocouple temperature sensor and multi-channel data acquisition card. The sensors and high-speed infrared thermometer are simultaneously used to measure the surface temperature change curves internal the wall coat of aero-engine respectively. The experimental results prove the feasibility of this integration method. And the simplified and clear mathematical formulas with high measurement accuracy facilitate the application of engineering, compared with the traditional analysis method.

关 键 词：热电偶 航空发动机 瞬态温度 积分方程法 

分 类 号：V231[航空宇航科学与技术—航空宇航推进理论与工程]