双燃烧室冲压发动机超声速混合层混合增强数值研究  

Numerical study on mixing enhancement for supersonic mixing layer in dual combustor ramjet

作　　者：晏至辉[1] 陈逖[1] 于江飞[1] 刘卫东[1] 

机构地区：[1]国防科学技术大学航天与材料工程学院,长沙410073

出　　处：《航空动力学报》2010年第4期821-828,共8页Journal of Aerospace Power

摘　　要：研究了具有双燃烧室冲压发动机超声速燃烧室工程背景的特定超声速混合层的混合增强措施——低速流入口加入沿流向振荡.研究结果表明:它对二维混合层的混合增强效果明显,加振荡后流场燃烧强度加大,但仍属于较弱燃烧强度;振荡频率决定着涡量聚集区域的位置和大小,振幅决定着涡量分配和聚集的均匀程度.Numerical simulations were carried out for a mixing enhancement measure-streamwise surge plus low velocity flow inlet-for specific supersonic mixing layer in dual combustor ramijet＇s（DCR＇s） supersonic combustor.The results show that,if streamwise surge is added at low velocity flow inlet,the positive impact on mixing enhancement is evident,and the burning intensity is increased,however it still belongs to weak combustion.The frequency determines the location and scale of vortices assembling region,and the swing determines uniform degree of distributed and assembled vortices.

关 键 词：双燃烧室 混合增强 混合层 超声速燃烧 数值模拟 

分 类 号：V231.3[航空宇航科学与技术—航空宇航推进理论与工程]