超燃冲压发动机隔离段中激波串演化发展过程研究  

Research of evolution of shock train in scramjet isolator

作　　者：黄伟[1] 罗世彬[1] 王翼[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,长沙410073

出　　处：《机械设计与制造》2010年第5期201-203,共3页Machinery Design & Manufacture

基　　金：国防科技大学优秀研究生创新资助项目(B070101);湖南省研究生科研创新资助项目(3206)

摘　　要：隔离段内流场波系结构对超燃冲压发动机进气道的启动起着重要的作用,它是衔接进气道和燃烧室的桥梁。采用二维耦合隐式NS方程和RNGk-ε湍流模型对二维超燃冲压发动机隔离段内流场进行了数值模拟,研究了其内部激波串的演化发展过程。结果表明:出口反压的升高可使激波串沿隔离段内流道往上游移动;伴随着激波串的前移和马赫盘的出现,隔离段壁面附近涡亦成对出现;随着隔离段出口反压的逐步升高,激波串强度逐渐增强,由斜激波逐步转变为正激波串、λ正激波,直至将激波串推出隔离段,造成进气道的不启动;等直隔离段相比单壁扩张隔离段和双壁扩张隔离段,其抗反压能力更强,更能有效隔离燃烧室压力对进气道工作状态的影响。Wave structures in the isolator play an important role in the starting of scramjet inlet;it is the bridge to connect inlet and combustor.Two-dimensional coupled implicit NS equations and RNG k-ε viscid models were used to simulate the flow field of two-dimensional scramjet isolator,the evolution of shock train was investigated.Results show that the improvement of back pressure makes the shock train move forward along the flow field of the isolator;eddy appears in double near the wall of isolator with the mach disk;with the increasing of back pressure,intensity of shock train will be greater,oblique shock wave will become normal shock train,then λ normal shock wave,and the shock train will be pushed out of the entrance of isolator,the inlet will be unstart.Isolator with equal section can resist the influence of back pressure more easily than that with one side expanded and that with both sides expanded,it can insulate the effect of pressure of combustor on the working condition of inlet more efficiently.

关 键 词：航空、航天推进系统 隔离段 激波串 超燃冲压发动机 

分 类 号：TH16[机械工程—机械制造及自动化] V235.21[航空宇航科学与技术—航空宇航推进理论与工程]