摘要
基于双轴混合排气涡扇发动机热力学模型,采用气动热力循环参数分析方法,计算分析了带有涡轮通道内燃烧室(TIB)涡扇发动机设计点的热力性能,研究比较了TIB对发动机高度特性、速度特性以及转速特性的影响。计算结果表明,采用TIB方法,虽然耗油率(TSFC)有一定增大,但发动机单位推力(ST)明显增大,发动机性能得到改善。
Based on the thermodynamics model of two-spool,mixed-flow turbofan engine,the design point performance of turbofan engine with turbine inter-blade burner（TIB） was calculated and analyzed by the parameter analysis of the air thermodynamics cycle.The effect of the TIB on the engine altitude,velocity and rotational speed,was studied and compared with conventional turbofan.The calculation results show that introducing the TIB,the specific thrust is obviously increased while the specific fuel consumption only increase appreciably,and the engine performance is improved.
出处
《航空发动机》
2010年第6期19-22,31,共5页
Aeroengine
基金
国家自然科学基金(51076065)
江苏省"六大人才高峰"高层次人才培养对象项目资助
关键词
涡轮风扇发动机
涡轮通道内燃烧室
超紧凑燃烧
单位推力
耗油率
turbofan engine
turbine inter-blade burner
ultra-compact combustor
specific thrust
specific fuel consumption
