一种基于双模态燃烧二元高超声速进气道研究  

Research on two-dimensional hypersonic inlet based on dual-mode combustion

作　　者：李航[1,2] 李博[1] 

机构地区：[1]南京航空航天大学能源与动力学院 [2]中国人民解放军92724部队

出　　处：《航空动力学报》2012年第7期1579-1587,共9页Journal of Aerospace Power

基　　金：南京航空航天大学基本科研业务费专项科研项目(NS2010040)

摘　　要：设计并研究了一种基于双模态燃烧的二元高超声速进气道.通过在进气道内设计一个隔板,将流道分为超声速通道和亚燃通道.采用数值模拟方法,研究了内压段肩部型面,隔板进口高度及水平位置,过渡段起始点及扩张角、下通道出口高度、隔板头部型面等几何设计参数对进气道性能的影响规律,并给出了参数选择建议.结果表明:在研究范围内,内压段肩部型面、隔板进口高度及水平位置和过渡段起始点对总压恢复系数影响较大;而隔板进口高度及头部型面、过渡段扩张角和下通道出口高度对抗反压能力有较大影响.Design and study of a two-dimensional hypersonic inlet based on dual-mode combustion was conducted. The duct was divided into a supersonic duct and a subsonic com- bustion duct by a splitter plate. The influence of the geometry parameters on the inlet per- formance was mainly studied by using numerical method. The geometry parameters included the profile of the shoulder, the height and position of splitter plate, the turning position and expansion angle of transition duct, the height of subsonic combustion duct and the shape of the head of splitter plate. Results indicate that the profile of the shoulder, the height and position of splitter plate, the turning position of transition duct have great effects on the to- tal pressure recovery coefficient, while the height of splitter plate, the shape of the head of splitter plate, the expansion angle of transition duct and the height of subsonic combustion duct have great effects on characteristics of back pressure.

关 键 词：高超声速进气道 双模态超燃冲压发动机 数值模拟 隔板 反压特性 

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]