双燃烧室冲压发动机三维隔板后缘构型数值研究  

Numerical Study for Three-dimensional Clapboard Models in Dual Combustor Ramjet

作　　者：于江飞[1] 晏至辉[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

出　　处：《弹箭与制导学报》2010年第4期108-112,共5页Journal of Projectiles,Rockets,Missiles and Guidance

摘　　要：文中对双燃烧室冲压发动机超燃室中多种三维隔板后缘构型对超声速混合层的影响进行了数值研究，并详细分析了较优构型的冷流和燃烧流场。隔板后缘为交错构型时诱导的流向涡大大促进了混合层增长，楔块顶点间隔越大，楔角增大，流向涡演化发展得越快。同时详细分析了较优隔板后缘构型的冷流流场结构和其扩展构型的三维燃烧流场结构，在计算区域后段，燃烧流场混合效果比冷流流场的略有增加。Numerical simulations are conducted for the effect of diverse models of three-dimensional clapboard structures on the growth of supersonic mixing layer in DCR＇s supersonic combustor. The flowfield for the most effective model is analyzed in detail. In the ease for interlaced back edges, derivational streamwise eddies greatly accelerate mixing layer. The wedge with a larger vertex interval and a bigger angle develops streamwise eddies more effectively. Development of streamwise eddies and locations of reacting regions are gained through detailed investigation of the flowfield of the most effective model and its expanded one. Combustion plays a little positive role in mixing in back segment of the calculating domain where there is the weak combustion.

关 键 词：双燃烧室 隔板 混合层 超声速燃烧 数值模拟 

分 类 号：V235.21[航空宇航科学与技术—航空宇航推进理论与工程]