近喷嘴区域燃烧流场可视化研究  

Visualization of Combustion Flowfield in Injector Nearfield

作　　者：高玉闪[1,2] 金平[1] 蔡国飙[1] 

机构地区：[1]北京航空航天大学宇航学院,北京100191 [2]西安航天动力研究所,陕西西安710100

出　　处：《推进技术》2013年第9期1209-1213,共5页Journal of Propulsion Technology

基　　金：国家'八六三'高技术资助项目

摘　　要：为进一步深入研究气-气掺混燃烧机理,在带可视化窗口的透明燃烧室中,采用高速摄影仪和数码相机获得了同轴剪切喷嘴、同轴双剪切喷嘴和旋流喷嘴近喷嘴区域的气氢/气氧燃烧火焰结构。结果表明:剪切式喷嘴火焰始于氧喷嘴出口端面,燃烧主要发生在气-气掺混剪切层当中,同轴双剪切喷嘴在出口形成两个剪切燃烧面;与剪切式喷嘴相比,旋流式喷嘴近喷嘴区域燃烧更加剧烈,当旋流数足够大时,将在中心形成稳定的燃烧回流区。In order to study the gas-gas mixing and combuslion mechanism deeply, gas-gas combustion flow field in a chamber with quartz windows was conducted utilizing gaseous oxygen and hydrogen as propel- lants. The flame structure near the exit of the coaxial injector, tri-coaxial injector and swirl injector were captured by high-speed photography and digital camera. The resuhs show that the gas-gas combustion occurs mainly in the mixing shear layer and the combustion flame develops from the injector post tip. The tri-coaxi- al injector has two shear combustion surfaces. Compared with the shear injector, the swirl injector burns more intensely. When the swirl number is large enough, a stable combustion recirculation zone may be formed in the center.

关 键 词：喷嘴 气-气燃烧 燃烧流场可视化 透明燃烧室 高速摄影 

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]