先进军用航空发动机燃烧室关键设计技术  

Key Design Techniques of Advanced Military Aircraft Engine Combustor

作　　者：丁伟[1] 于向财 唐岩辉 

机构地区：[1]海军驻西安地区航空军事代表室,陕西西安710038 [2]海军航空兵学院,辽宁葫芦岛125001

出　　处：《航空科学技术》2014年第4期1-6,共6页Aeronautical Science & Technology

摘　　要：随着未来先进军用航空发动机向着更高推重比、更低耗油率、更高机动性等方向发展,燃烧室则向着更高温升和热容方向发展,为燃烧室的燃烧稳定性、可靠性、耐久性的提高和寿命期成本的降低提出挑战。先进的燃烧组织技术和火焰筒冷却、结构技术是保证高性能航空发动机燃烧室能够满足设计要求的关键。目前主要的燃烧室关键技术包括驻涡燃烧组织技术,多斜孔气膜冷却火焰筒、浮动壁火焰筒、多孔层板冷却火焰筒等火焰筒冷却与结构技术。本文综述了这些技术的研究现状及未来发展。As the future advanced military aircraft engine developes toward a higher thrust to weight ratio, lower fuel consumption, higher mobility, the combustor developes toward a higher temperature rise and heat capacity, which are more dififcult to improve combustion stability, reliability, durability and reduce life-cycle costs. Advanced organization combustion technology, cooling and structure technologies of the lfame tube are the key, which are to ensure that current and future high performance aircraft engein combustor can meet the design requirements. At present, the main combustion chamber key technologies are trapped vortex organization combustion technology and some lfame tube cooling and construction technologies, which are including the inclined multi-hole iflm cooling lfame tube, lfoat wall liner and Lamilloy/Transply cooling lfame tube. This article reviewed the research status of these technologies and future development.

关 键 词：发动机 驻涡燃烧室 多斜孔气膜冷却 浮动壁火焰筒 多孔层板冷却 

分 类 号：V23[航空宇航科学与技术—航空宇航推进理论与工程]