摘要
针对某高超声速飞行器飞行任务对低速推进系统的需求(Ma≤3.5),以某小涵道比加力混排涡扇发动机为背景机提出了两套布局方案.研究结果表明:对于加力涡扇发动机(TF)方案,通过对背景发动机控制规律的优化,能有效降低发动机在高空大马赫数工作状态时混合器内外涵的总压差异,并且能获得更低的发动机单位耗油率.对于加力涡扇/亚燃冲压并联组合发动机方案,与TF方案相比,进气道和喷管的各自独立使其在结构上更加复杂,质量会大大增加,技术风险加大.
Two sets of propulsion concept were analyzed based the existent low bypass ratio augmented turbofan engine with mixed exhaust nozzle,in order to meet the mission requirements on the low Mach propulsion system(Ma≤3.5) in the hypersonic transportation.The result shows: as for the turbofan(TF) concept,by means of optimizing the control law of the base turbofan engine,total pressure difference between the two streams at the mixed zone was effectively reduced,contributing to flow organization at the afterburner ...
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
2009年第7期1564-1569,共6页
Journal of Aerospace Power
关键词
高超声速飞行器
混排加力涡扇发动机
涡扇冲压组合发动机
hypersonic transportation
mixed flow augmented turbofan engine
turbofan/ramjet combine cycle engine
