摘要
针对新一代高油气比(0.051及以上)航空发动机燃烧室,本文提出头部采用化学恰当比直接混合燃烧设计方案。对于新一代高压比(70及以上)低排放民用航空发动机燃烧室,由于其自着火延迟时间极短,因此采用贫油直接混合燃烧,而不能采用预混合预蒸发燃烧。本文提出了一种贫油直接混合低排放燃烧室方案,其燃油空气模由简单的压力雾化喷嘴和轴向旋流器组成,结合燃油分级技术降低污染物排放,该燃烧室具有较好的燃烧稳定性。这两类燃烧室的燃烧空气分数非常大,因此存在慢车贫油熄火问题。文中针对两类燃烧室分别提出了相应的解决方案,同时介绍了火焰筒外壁面及内壁面的冷却设计方案。本文研究成果可为下一代航空发动机燃烧室的发展提供指导作用。
New generation military aero-combustor is high(FAR)(0.051 and above)combustor.It is stoichiometric direct mixing combustion.Fuel air module design configuration is proposed.New generation civil aero combustor is high pressure(such as pressure ratio 70 and above)low emissions combustor.Because of extremely short autoignition delay time,it cannot be premixed combustion,must be lean direct mixing(LDM)combustion.By combination of simple pressure swirl fuel nozzle and axial air swirler as basic fuel air combustion design,with the whole combustor the configuration,with fuel staging,the emissions are good without combustion instability problem.Both combustors use very high combustion air fraction,thus there is an idle lean blow out(LBO)issue.Design approaches to solve idle LBO problem are proposed for both type combustors.New liner cooling design is presented for outer liner and inner liner.The results of this study will provide guideline for the development of next generation aero combustors.
作者
金如山
党进
刘富强
CHIN Ju-Shan;DANG Jin;LIU Fu-Qiang(AIAA Associate Fellow,Laguna Woods,California 92637,USA;Fossil Energy Research Corp.,Laguna Hills,California 92653,USA;Laboratory of Light-duty Gas-turbine,Institute of Engineering Thermophysics,Chinese Academy of Sciences,Beijing 100190,China;University of Chinese Academy of Sciences,Beijing 100049,China)
出处
《工程热物理学报》
EI
CAS
CSCD
北大核心
2022年第2期543-552,共10页
Journal of Engineering Thermophysics
