旋转爆震发动机燃烧室气膜出流影响数值研究  

Numerical study on effect of film ejections in rotating detonation engine combustor

作　　者：王元帅 谭晓茗[1] 田佳 张靖周[1] WANG Y uanshuai;TAN Xiao ming;TIAN Jia;ZHANG Jingzhou(College of Energy and Power Engineering,Nanjing University of Aeronautics and Astronautics,Nanjing 210016,China)

机构地区：[1]南京航空航天大学能源与动力学院,南京210016

出　　处：《航空动力学报》2021年第11期2353-2362,共10页Journal of Aerospace Power

摘　　要：针对旋转爆震发动机(RDE)壁面的高热负荷问题,开展旋转爆震发动机燃烧室壁面气膜冷却的数值仿真,探究气膜出流与爆震波、斜激波和燃烧室流场之间的相互作用以及气膜对壁面的冷却特性。研究结果表明:爆震波对气膜的压缩和冷却孔的堵塞作用明显,气膜对爆震波整体的传播特性影响较小。受爆震波和燃烧室流场的影响,气膜出流存在周期性的摆动情况,这在一定程度上影响了壁面的冷却效果。在爆震波覆盖的壁面区域,峰值壁温下降程度有限,但时均壁温的降幅超过26.9%;在斜激波覆盖区域,随着冷气量的增加,峰值壁温和时均壁温的降幅超过32.5%和51.3%,气膜对该区域壁面的冷却效果更加明显。To solve the problem of high thermal load on the wall of the RDE(Rotating Det-onation Engine),a numerical simulation of film cooling on the combustor wall of an RDE was carried out to explore the interaction between film outflow and detonation wave,oblique shock wave and flow field,as well as the film cooling characteristics on RDE wall.The results showed that the detonation wave had an obvious effect on the compression of the film and blockage of the cooling holes.The film had little effect on the overall propagation characteristics of the detonation wave.Affected by the detonation wave and the flow field of the combustor,the film outflow had periodic oscillations,which affected the cooling effect of the wall to a certain extent.Under the film cooling,the decrease of peak wall temperature was limited in the area covered by the detona-tion wave,but the decrease of time-average wall temperature was more than 26.9%.In the area covered by the oblique shock wave,with the increase of cooling air quantity,the decrease of peak wall temperature and time average wall temperature was more than 32.5%and 51.3%,re-spectively,and the cooling effect of the film on the wall covered by oblique shock wave became more significant.

关 键 词：旋转爆震发动机 爆震波 气膜冷却 壁面温度 冷却效果 

分 类 号：V231.1[航空宇航科学与技术—航空宇航推进理论与工程]