折流燃烧室几何结构简化和流量统计对比  

Simplification and Flow Rate Statistics Comparison of Slinger Combustor

作　　者：王方[1] 甘甜 王煜栋 金捷[1] WANG Fang;GAN Tian;WANG Yu-dong;JIN Jie(School of Energy and Power Engineering,Beihang University,Beijing,China,100191)

机构地区：[1]北京航空航天大学能源与动力工程学院,北京100191

出　　处：《热能动力工程》2023年第5期24-29,共6页Journal of Engineering for Thermal Energy and Power

基　　金：国家自然科学基金(91741125);国家科技重大专项(2017-I-0004-0005)。

摘　　要：针对航空发动机燃烧室的高保真数值模拟需求,基于自研软件AECSC-IBM对某型带甩油盘的折流燃烧室的简化结构几何模型和高保真几何模型进行冷态工况数值模拟。结果表明:该折流燃烧室在几何结构上的不同会使得燃烧室的流量分配和流场结构出现差异,在流量分配上简化结构几何模型的3股气流占比分别是16.26%,26.74%和57%,高保真几何模型3股气流占比分别是21.23%,17.58%和61.19%;在流场结构上,高保真折流燃烧室的主燃区位置靠近火焰筒外壳前端,而简化结构折流燃烧室的主燃区域明显靠后。In order to meet the requirements of high-fidelity numerical simulation of aero-engine combustion chambers,the self-developed software AECSC-IBM simulates the simplified structural geometric model and high-fidelity geometric model of a certain type of slinger combustor under cold working conditions numerically in this paper.The results show that the difference in the geometry of the slinger combustor will make the flow distribution and flow field structure of the combustor different.For flow distribution,the proportions of the three streams in the simplified geometric model are 16.26%,26.74%and 57%respectively,and the proportions of the three streams in the high-fidelity geometric model are 21.23%,17.58%and 61.19%respectively;for the flow field structure,the main combustion zone of the high-fidelity slinger combustor is close to the front end of the flame tube shell,while the main combustion zone of the simplified structure slinger combustor is obviously backward.

关 键 词：折流燃烧室 高保真建模 大涡模拟(LES) 流量分配 

分 类 号：V231.2[航空宇航科学与技术—航空宇航推进理论与工程]