两种超声速燃烧室内氢气燃烧的三维数值研究  

3-D numerical investigation on supersonic combustion of hydrogen in two different type of scramjet combustors

作　　者：周建兴[1] 朴英[1] 岂兴明[1] 祝剑虹[1] 陈美宁[1] 

机构地区：[1]清华大学航天航空学院,北京100084

出　　处：《航空动力学报》2008年第3期470-475,共6页Journal of Aerospace Power

摘　　要：通过隐式耦合求解可压缩N-S方程及组分方程,对台阶喷射燃烧室和支杆喷射燃烧室内的流场进行了三维数值研究.研究结果表明,支杆喷射燃烧室喷入氢气,在整个流道内产生的流向涡和横向涡更加强烈,更加能够促进氢气和空气在流向的对流掺混和扩散掺混效果,从而使得燃烧室内的掺混距离缩短;同时,这两个超声速燃烧室内的凹槽结构能起到增强掺混和稳定火焰的作用,使燃烧室后部燃烧区域增大.The flow fields of hydrogen injected into combustors with step injectors and strut injectors were numerically investigated by solving the 3-D compressible Navier-Stokes and species equations with implicit finite volume method. The results show that because of the stronger streamwise and spanwise vortexes induced by the hydrogen flows injected via the strut injectors, hydrogen/air mixing efficiency is greatly enhanced and the mixing length along the channel is shortened. Besides, the cavities in both types of combustors enable the fuel to be mixed more fully and also stabilize the flame, enlarging the combustion area in the rear parts of the combustors.

关 键 词：航空 航天推进系统 超声速燃烧 氢气 流向涡 掺混效果 数值研究 

分 类 号：V231.26[航空宇航科学与技术—航空宇航推进理论与工程]