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.

V231.2

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