航空发动机地面进气加温试验  

Aeroengine Ground-level Test with Inlet Air Heating

作　　者：刘作宏 何志强 柳国印 刘佳鑫 康忱 程鲁 LIU Zuo-hong;HE Zhi-qiang;LIU Guo-yin;LIU Jia-xin;KANG Chen;CHENG Lu(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3期148-153,共6页Aeroengine

基　　金：航空动力基础研究项目资助。

摘　　要：为了模拟发动机进气加温试验,开展了发动机地面试车台进气加温试验研究,设计了一套合理的进气加温设备,并提出了进气加温试验测试方案和试验方法。结果表明:在108.88℃进气温度下,高温区角度为180°,高温区主要分布在0°和180°位置,低温区分布在90°和270°位置,隔开了连续高温区,高温区平均温度和面平均温度差值较小,温度周向不均匀度为0.43%,温度分布均匀,不存在强烈温度畸变情况;在进气温度从94.82℃上升至108.88℃时用时80 s,高温区温升率为0.18℃/s,时间域内的温度畸变较小,裕度损失小,温场无旋转,高温区分布和周向温度不均匀度均不随时间变化产生明显改变;在进气温度从65.34℃升至108.88℃时,周向分布保持均匀,建立了面平均温度、高温区面平均温度的线性关系。获得了台架温场均值与发动机控制系统采集进气温度的关系。In order to conduct engine inlet heating simulation tests,an inlet heating test was carried out on a ground-level test bed,a set of suitable inlet heating equipment was designed,and the inlet heating testing scheme and test method were proposed.The results show that at the inlet temperature of 108.88℃,the circumferential extent of the high-temperature region was 180°,the high-temperature regions were mainly distributed at 0°and 180°,the low-temperature regions were distributed at 90°and 270°,separating the high-temperature regions.The difference between the average temperature in the high-temperature regions and the area-weighted face-average temperature was small,and the circumferential temperature distortion intensity was 0.43%,indicating a uniform temperature distribution and no strong temperature distortion;it took 80 seconds for the inlet temperature rose from 94.82℃to 108.88℃,and the temperature rise rate of hightemperature region was 0.18℃/s,the time-variant temperature distortion was small,the stability margin loss was small,the temperature field was irrotational,and the distribution of high-temperature regions and the circumferential temperature distortion intensity did not show significant changes obviously with time.When the inlet temperature rose from 65.34℃to 108.88℃,the circumferential distribution remained uniform,and the linear relationship between the area-weighted face-average temperature and the area-weighted average temperature of the high-temperature regions was established.The relationship between the area-weighted face-average temperature and the inlet air temperature acquired by the engine control system was obtained.

关 键 词：进气加温 地面试验 温场 温度畸变 航空发动机 

分 类 号：V211.73[航空宇航科学与技术—航空宇航推进理论与工程]