An Experimental Investigation on Combustion Characteristics of Hypermixer Injectors - Effects of the ‘Swept’ Applied to Hypermixer Injector Ramps

摘要：

　　Supersonic mixing and combustion enhancement is the key technology for success of the development of the scramjet engine.In this study,some types of hypermixer(ramp)injectors were investigated by the combustion test.Especially,we have focused on the effect of applying swept to these injector ramps in this paper.According to the experimental result,there was little difference on the thrust performance due to the application of swept when streamwise vortices was strongly generated.When streamwise vortices were not introduced enough,swept type injectors were better thrust performance than unswept type.

关键词： Hydrogen fueled scramjet Supersonic combustion Streamwise vortices Hypermixer Boundary layer sepration

作者: Noritsugu Kubo Atsuo Murakami Kenji Kudo Sadatake Tomioka

作者单位: Department of Aerospace Engineering,Tohoku University,6-6-01,Aramaki-Aza-Aoba,Sendai,980-8579,Japan Kakuda Space Center,Japan Aerospace Exploration Agency,Kakuda,981-1525,Japan Department of Aerospace Engineering,Tohoku University,6-6-01,Aramaki-Aza-Aoba,Sendai,980-8579,Japan;

会议类型: 国际会议

会议名称: 2014 Asia-Pacific International Symposium on Aerospace Technology(2014亚太航空航天技术学术会议)

会议地点: 上海

会议语种:英文

页码: 1-7

在线出版日期: 2014-09-24（万方平台首次上网日期，不代表论文的发表时间）