舰载涡扇发动机高低温起动试验与分析  

High and low temperature starting test and analysis of carrier-based turbofan engine

作　　者：邢洋 杨怀丰 刘亚君 江井跃 张伟 XING Yang;YANG Huaifeng;LIU Yajun;JIANG Jingyue;ZHANG Wei(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,辽宁沈阳110015

出　　处：《推进技术》2024年第1期236-242,共7页Journal of Propulsion Technology

摘　　要：为验证某舰载涡扇发动机在高低温环境条件下起动特性,基于高低温起动验证试车台,通过模拟高低温进气和保温条件,开展了采用RP-3燃油和RP-5燃油的涡扇发动机高低温起动性能对比试验。分析了不同环境温度下发动机起动点火性能的变化规律;对比了不同环境温度、燃油种类、转速上升率对发动机起动性能的影响。试验结果表明,大气温度由60℃下降到-20℃,主燃烧室供油到点着火时间延长约1~2 s;在-20~60℃内,采用RP-3和RP-5两种燃油,发动机起动性能基本一致;给定转速上升率降低0.1%/s,低温起动时间延长0.01~0.06(相对值),在高压换算转速n_(Hcor)=0.3~0.5(相对值)转速范围内,反馈转速上升率与给定上升率最大差异为28.2%;整个起动转速范围内,主燃油供油流量最高下降10.8%,燃油总管压力p_(f)与高压压气机出口压力p_(31)之差最高下降10.1%。In order to verify the starting characteristics of the carrier-based turbofan engine in high and low temperature environment,a comparative test of the engine's high and low temperature starting performance using RP-3 and RP-5 fuel was carried out based on the high and low temperature starting verification test stand by sim⁃ulating the high and low temperature intake and insulation conditions.The variation law of ignition performance of engine starting under different environmental temperatures is analyzed.The effects of ambient temperature,fuel type and speed rise rate adjustment on engine starting performance were compared.The test results show that when the atmospheric temperature drops from 60℃to-20℃,the time of starting fuel supply to ignition point is prolonged by about 1~2 s.In the range of-20℃~60℃,using the above two fuels,the engine starting perfor⁃mance is basically the same.If the given speed rise rate is lowered by 0.1%/s,the low temperature starting time is prolonged by 0.01~0.06(relative value).Within the range of high-pressure conversion speed n_(Hcor)=0.3~0.5(rela⁃tive value),the maximum difference between the feedback speed rise rate and the given rise rate is 28.2%.In the whole range of starting speed,the maximum drop of main fuel supply flow rate is 10.8%,and the difference be⁃tween the fuel manifold pressure p_(f) and the high-pressure compressor outlet pressure p_(31) decreases by a maximum of 10.1%.

关 键 词：舰载涡扇发动机 高低温起动 起动性能 转速上升率 燃油 

分 类 号：V231.3[航空宇航科学与技术—航空宇航推进理论与工程]