航空发动机新型补燃增推燃烧室的现状与发展  

Present and Future Development of Advanced Second Burner for Aeroengine

作　　者：梁春华[1] 杨东丹[1] 刘红霞[1] 尚守堂[1] 

机构地区：[1]中航工业沈阳发动机设计研究所,沈阳110015

出　　处：《航空发动机》2012年第5期1-5,17,共6页Aeroengine

摘　　要：涡轮后框架一体化加力燃烧室(简称涡轮后框架燃烧室)和涡轮间燃烧室均是为了提高推进效率和降低耗油率而新近开发和验证的2种先进补燃增推燃烧室。综述了2种燃烧室的基本结构、研制背景、发展历程和目前研究进展,总结了从众多研究中获得的这2种燃烧室相对常规结构的性能特点,如涡轮后框架燃烧室结构紧凑,流体损失小,结构耐久性好;涡轮间燃烧室推进效率高,热效率高。还指示了这2种燃烧室的发展趋势。Integrated turbine rear frame afterburner and Inter-stage Turbine Burner （ITB） are advanced augmented burners recently developed and demonstrated in order to improve propulsive efficiency and reduce specific fuel consumption. Their basic structures, development background and progress and current state burners were overviewed. The results obtained from the issued documents show that the performance characteristics with compact structure, low flow loss and high endurance are demonstrated for integrated turbine rear frame afterburner and the performance characteristics with high thrust and thermal efficiency are demonstrated for ITB. Their future trend are forecasted.

关 键 词：补燃增推燃烧室 涡轮后框架燃烧室 涡轮间燃烧室 性能 航空发动机 

分 类 号：V235.113[航空宇航科学与技术—航空宇航推进理论与工程]