激波对超声速流中横向射流的影响  

Shock Impinge on Supersonic Cross Flow Injection

作　　者：潘余[1] 王振国[1] 

机构地区：[1]国防科技大学航天与材料工程学院,湖南长沙410073

出　　处：《国防科技大学学报》2007年第6期6-9,共4页Journal of National University of Defense Technology

基　　金：国家863高技术资助项目(2005AA721051)

摘　　要：为了揭示激波对超声速流中横向射流的影响,在超声速流中利用长9mm、坡度为23°的斜坡产生激波。组合利用高速摄影仪和纹影仪拍摄激波入射在气体和液体射流的不同位置,以及相同位置不同喷注压降时的流场纹影和阴影图像。结果表明,激波对气体和液体横向射流的影响基本相同,都表现为入射激波增强了湍流度,扩大了燃料空间发展区域,增强了与主流的混合,激波入射在射流的前部比射流的后部影响大。To investigate the shock impingement on vertical injection in supersonic flow, shock was produced by a 9mm long, 23° angle wedge. The images of shocks impinged at different position and pressure of gas and liquid injection were achieved by using both a high speed cantata and a schlieren system. Results revealed that gas and liquid injection almost have similar phenomena, that is, impinged by the shock, fuel tttrbulent intensity will increase, fuel distribution area will be larger in supersonic flow, spreading more quickly into the main supersonic flow, and the shock impinged at the foreside affect mere than rearward of injection.

关 键 词：超声速燃烧冲压发动机 横向射流 激波 

分 类 号：V235.213[航空宇航科学与技术—航空宇航推进理论与工程]