摘要
通过气动热力学方法建立了一种双外涵组合排气变循环发动机总体性能仿真模型,编制了相应总体性能仿真程序,模拟生成两种构型模式下节流状态和最大状态最佳变几何方案。研究表明,仅构型可变的条件下,节流过程中双外涵模式较单外涵模式耗油率降低0.7%~2.5%,推力降低3.1%~5.5%。仅部件几何可变的条件下,主喷管、混合器和高压涡轮导向器的组合变几何方案(方案4)性能收益相对最高。较主喷管几何单独可变方案(方案1),变几何方案4节流状态耗油率降低2.7%~3.2%,高空最大状态推力提高4.2%~5.2%。采用双外涵变构型和变几何方案4组合的变循环方案性能收益可进一步提高。以主喷管单独可调的单外涵发动机性能参数为基准,该变循环方案节流状态耗油率降低4%,高空最大状态推力提高5.2%;以主喷管单独可调的双外涵发动机性能参数为基准,该变循环方案节流状态耗油率降低3.2%,高空最大状态推力提高13.7%。
A performance simulation model of dual-bypass combined exhaust VCE was established by means of aerothermodynamics,and the performance simulation program was compiled to simulate the optimal variable geometry scheme in throttling state and maximum state under two configuration modes.The results showed that the specific fuel consumption of dual-bypass mode was lower 0.7%−2.5%and the thrust was lower 3.1%−5.5%than that of single bypass mode when the configuration was only variable.Performance benefit of the combined variable geometry scheme(scheme 4)with main nozzle,mixer and high-pressure turbine guide was the highest when the components geometry was only variable.Compared with the variable geometry scheme(scheme 1)of only variable main nozzle geometry,the specific fuel consumption under throttling condition of scheme 4 was reduced by 2.7%−3.2%,and the maximum thrust at high altitude was increased by 4.2%−5.2%.Performance benefit of the variable cycle scheme with combination of dual-bypass variable configuration and variable geometry scheme 4 can be further improved.Based on the performance of single bypass engine with individually adjustable main nozzle,the specific fuel consumption under throttling condition of the variable cycle scheme was reduced by 4%,and the maximum thrust at high altitude was increased by 5.2%.Based on the performance of dual-bypass engine with individually adjustable main nozzle,the specific fuel consumption under throttling condition of the variable cycle scheme was reduced by 3.2%,and the maximum thrust at high altitude was increased by 13.7%.
作者
牟园伟
王奉明
朱大明
MU Yuanwei;WANG Fengming;ZHU Daming(Aero Engine Academy of China,Aero Engine Corporation of China,Beijing 101304,China)
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
2023年第5期1114-1122,共9页
Journal of Aerospace Power
基金
先进航空动力创新工作站(HKCX2020-02-004)。
关键词
变循环发动机
变几何
双外涵
仿真模型
耗油率
variable cycle engine
variable geometry
dual-bypass
simulation model
specific fuel consumption
