Mixing Enhancement in a RBCC Engine Operating in Hypersonic Flow

摘要：

　　From the Mach 11 flight condition experiment result at HIEST,it was found that it was necessary to enhance mixing to raise combustion efficiency.Therefore,the mixture state in the engine was investigated.The experiment conducted at supersonic wind tunnel.The mixture state was evaluated by gas sampling by the experiment without combustion.As a result,in the case of the compression ramp,the rocket exhaust was entrained into streamwise vortices generated by the compression ramp.Mixing enhancement effect is match higher with the compression ramp than the base condition.Additionally,in the case of the rocket with slit,airflow was entrained between two rocket exhaust.Mixing enhancement effect is match higher with the rocket with slit than the base condition.It is possible and effective to apply the mixing enhancement devices using streamwise vortices studied in the cold flow to the mixing enhancement in RBCC engine.

关键词： RBCC engines Hypersonic Flow Shear Layer

作者: Ryosuke Nakano Sadatake Tomioka Noritsugu Kubo Atsuro Murakami Kenji Kudo Shuichi Ueda

作者单位: JAXA Kakuda Space Center,Kakuda,Japan Department of Aerospace Engineering,Tohoku University,Sendai,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）