2种涡轮燃烧形式的涡扇发动机性能研究  

Performance Study of Turbofan Engine with Two Forms of Combustion in Turbine

作　　者：徐兴亚[1] 唐豪[1] 郑海飞[1] 唐文彬[1] 

机构地区：[1]南京航空航天大学能源与动力学院,南京210016

出　　处：《航空发动机》2013年第5期37-41,46,共6页Aeroengine

基　　金：国家自然科学基金(51076064)资助

摘　　要：为了研究不同涡轮燃烧形式对大涵道比涡扇发动机的性能影响,在传统发动机数学模型的基础上,分别加入各型涡轮燃烧结构的热力学计算模型,分析比较了在不同工作过程参数下,4种带涡轮燃烧结构发动机与传统发动机的性能(单位推力和单位燃油消耗率)随风扇增压比、高压压气机增压比、高压涡轮进口总温和涵道比的变化关系。结果表明:涡轮级间燃烧室(ITB)与涡轮叶间燃烧室(TIB)各有特点,但都能够明显提高传统分别排气涡扇发动机的性能,其中高压涡轮叶间燃烧室(HTIB)效果尤为突出。In order to study the influence of different technical schemes of combustion in turbine on a high bypass ratio turbofan engine, by adding each thermodynamic model of combustion in turbine to the mathematical model of traditional engine. The relations between engines with combustion in turbine and traditional engine in different parameters （on- design） were calculated and compared as fan pressure boost ratio, high pressure compressor pressure boost ratio, high pressure turbine inlet total temperature and bypass ratio. The results show that： Inter-Turbine Burner （ITB） and Turbine Inter-Blade Burner （TIB） have different features. Both of them can significantly improve the performance of traditional separate-flow turbofan engine, and the effect of High pressure Turbine Inter-Vane Burner （HTIB） is particularly prominent.

关 键 词：涡轮叶间燃烧室 涡轮级间燃烧室 性能参数 热力循环 数学模型 

分 类 号：V235.13[航空宇航科学与技术—航空宇航推进理论与工程]