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.
出处
《航空动力学报》
EI
CAS
CSCD
北大核心
2010年第4期821-828,共8页
Journal of Aerospace Power
关键词
双燃烧室
混合增强
混合层
超声速燃烧
数值模拟
dual combustor
mixing enhancement
mixing layer
supersonic combustion
numerical simulation