| 摘要: |
| 为深入了解航空发动机折流燃烧室内部复杂流场结构，对一种带有离心甩油盘的单头部环形折流燃烧室冷热态流场进行大涡模拟。数值计算模拟了从启动状态到稳定燃烧状态的完整非稳态过程，获得了该燃烧室流量分配、压力损失等参数以及冷热态流场结构。数值计算结果表明：（1）冷热态下燃烧区流场结构分为主回流区和次回流区两部分，主回流区冷态时呈现多涡结构，热态时回流区形状受燃油射流影响呈现对称的双涡结构；（2）燃烧室中各涡团结构由各进气孔射流相互作用形成，涡团结构促进燃烧室内部的能量和质量交换；（3）热态时燃烧室前后涡流板周围存在两个稳定的点火源。 |
| 关键词: 折流燃烧室 大涡模拟 流场 多涡结构 稳定点火源 |
| DOI：10.13675/j.cnki.tjjs.210748 |
| 分类号:V231.2 |
| 基金项目:国家科技重大专项（2017-III-0006-0031)。 |
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| Large Eddy Simulation of Combustion Flow Field in a Slinger Combustor |
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ZHAO Yi-yu1, DUAN Zheng-liang1, CAI Wen-zhe2, ZHANG Teng1, YAN Ying-wen1
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1.College of Energy and Power Engineering,Nanjing University of Aeronautics and Astronautics,Nanjing 210016,China;2.College of Energy and Power Engineering,Beijing University of Aeronautics and Astronautics,Beijing 100191,China
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| Abstract: |
| In order to investigate the complicated flow filed structure in aero slinger combustor， large eddy simulation （LES） was used to explore both the cold and combustion flow field of a single-dome annular slinger combustor with centrifugal fuel injection. The complete unsteady process from starting status to stable combustion was simulated， in which mass flow distribution， pressure loss and flow field structures of the combustor were obtained. The results show that： （1） The combustion zone can be divided into a primary recirculation zone and a secondary recirculation zone. The primary recirculation zone shows a structure of multi-vortex for the cold flow field， but the primary recirculation zone is a symmetrical vortex structure that affected by the jet of kerosene for the combustion flow field. （2） Vortexes， formed by the interaction of the air inlet jet， promote the exchange of energy and mass. （3） There are two stable ignition sources around the vortex plate under the combustion status. |
| Key words: Slinger combustor Large eddy simulation Flow field Multi-vortex structure Stable ignition sources |
