加力燃烧振荡高温宽频动态压力测试  

High-Temperature and Wide-Frequency Dynamic Pressure Measurement Techniques for Afterburner Combustion Oscillation

作　　者：李中玺 邢志国 于大洋 宋伟锋 张天昊 LI Zhong-xi;XING Zhi-guo;YU Da-yang;SONG Wei-feng;ZHANG Tian-hao(AECC Shenyang Engine Research Institute,Shenyang 110015,China)

机构地区：[1]中国航发沈阳发动机研究所,沈阳110015

出　　处：《航空发动机》2024年第4期156-161,共6页Aeroengine

基　　金：航空动力基础研究项目资助。

摘　　要：针对发动机加力燃烧室振荡燃烧动态压力测试受到温度及频响限制问题,描述了管腔效应机理,比较了使用传感器齐平安装、共振管以及半无限长管3种动态测量系统的优缺点,进行了压力脉动受感部的动态频响特性测试。分析了在管腔长度不变的条件下共振管管腔内径变化对管腔频率和幅值的影响;对于半无限长管系统,在半无限长管长度不变的条件下比较了3种管腔长度对加力脉动受感部管腔频率和幅值的影响;在管腔长度不变的条件下比较了2种半无限长管长度对受感部频率和幅值的影响。结果表明:管腔长度为55.3 mm、管腔内径为3.5 mm、半无限长管长度为15 m是高温宽频加力脉动测试的最优方案。为削弱管腔效应的影响,利用经温度补偿的系统传递函数实现了在2000 Hz内对早期加力动态压力测试数据的修正。Aiming at the problem of temperature and frequency response restrictions in dynamic pressure measurement of the afterburner combustion oscillation of an aeroengine,the mechanism of tube cavity effect is described,the advantages and disadvantages of dynamic measurement systems using the flush-mounted sensor,resonant tube,and semi-infinite tube are compared.The amplitudefrequency response characteristics of these dynamic pressure sensing systems were experimentally studied.For the resonant tube systems,the influence of the tube's inner diameter on the resonant frequency and amplitude was experimentally investigated while keeping tube lengths constant.For the semi-infinite tube systems,the effects of mounting length and termination length on the resonant frequency and amplitude were experimentally studied under the conditions of three different mounting lengths and two termination lengths.According to the experimental results,the optimal configuration for a high-temperature wide-frequency afterburner dynamic pressure measurement system is the semi-infinite tube system with a mounting length of 55.3 mm,an inner diameter of 3.5 mm,and a termination length of 15 m.To weaken the tube cavity effect,the temperature-compensated system transfer functions were used to correct previous afterburner pressure measurement data within 2000 Hz.

关 键 词：动态压力测试 管腔效应 加力燃烧振荡 航空发动机 

分 类 号：V263.3[航空宇航科学与技术—航空宇航制造工程]