喷嘴结构细节对连续爆轰发动机掺混特性的影响  

Influence of injector structure details on mixing characteristics of continuous detonation engine

作　　者：孔维鹏 刘倩 KONG Weipeng;LIU Qian(Beijing Aerospace Propulsion Institute,China Aerospace Science and Technology Corporation,Beijing 100076,China;Laboratory of Cryogenic Liquid Propellants,China Aerospace Science and Technology Corporation,Beijing 100076,China)

机构地区：[1]中国航天科技集团有限公司北京航天动力研究所,北京100076 [2]中国航天科技集团有限公司低温液体推进技术实验室,北京100076

出　　处：《航空动力学报》2024年第8期178-184,共7页Journal of Aerospace Power

摘　　要：为研究不同喷嘴结构细节对气氢/气氧连续爆轰发动机冷态掺混特性的影响,采用商业软件Fluent对其冷态掺混流场进行了数值仿真研究。以环缝-喷孔式喷注结构为基础,设计了12种不同喷嘴结构的连续爆轰发动机,研究了在入口条件相同的情况下,不同气氧喷嘴出口扩张角、不同气氢喷注角度、不同气氢喷嘴出口扩张角以及单双侧喷注对掺混特性的影响。结果表明:气氧喷嘴出口扩张角在0°~20°范围内,掺混效果呈现先下降后上升的趋势,气氧喷嘴出口扩张角最佳值为20°;气氢喷注角度在30°~90°范围内,掺混效果呈现先上升后下降的趋势,气氢喷注角度最佳值为45°;在0°~10°范围内,增大气氢喷嘴出口扩张角使得掺混效果下降;气氢双侧喷注的掺混效果明显优于单侧喷注。In order to study the influence of different injector structure details on the cold mixing characteristics of GH2/GO2 continuous detonation engine,the cold flow field of GH2/GO2 continuous detonation engine was numerically simulated with commercial software Fluent.Based on the annular-hole injector structure,12 different engines with different injector structures were designed.The influences of different oxygen injector outlet expansion angles,different hydrogen injection angles,different hydrogen injector outlet expansion angles,and unilateral injection on the mixing characteristics were studied under the same inlet conditions.The results showed that the mixing effect decreased first and then increased when the expansion angle of oxygen injector outlet was within the range of 0°-20°,and the optimum expansion angle was 20°.When the hydrogen injection angle was within the range of 30°-90°,the mixing effect increased first and then decreased,and the optimal injection angle was 45°.Within the range of0°-10°,increasing the expansion angle of the hydrogen injector outlet reduced the mixing effect.The mixing effect of gas-hydrogen bilateral injection was obviously better than that of unilateral injection.

关 键 词：连续爆轰发动机 气氢/气氧 喷嘴结构 冷态流场 掺混特性 数值仿真 

分 类 号：V430[航空宇航科学与技术—航空宇航推进理论与工程]