摘要
针对未来高推重比涡扇发动机的高、低压涡轮功分配问题,进行了总体性能设计研究,并与常规布局涡扇发动机进行对比分析,归纳出其设计难点;提出了2种解决途径,即改变压缩系统的结构形式和采用涡轮间燃烧技术。
Aiming at power distribution of future high thrust-weight ratio engine high and low pressure turbine, the general performance design was conducted and compared with that of the conventional turbofan engine, the design difficulties were summarized. Two solutions about changing compression system structure and adopting interstage turbine combustion technology were proposed.
出处
《航空发动机》
2012年第1期13-16,20,共5页
Aeroengine
关键词
涡扇发动机
总体性能
耗油率
单外涵
双外涵
涡轮间燃烧
turbofan engine
general performance
fuel consumption
single-bypass
double-bypass
interstage turbine combustion
