气液喷流与超声速凹腔流场的相互作用  

Interaction between gas/liquid injection and supersonic flow over cavities

作　　者：房田文[1] 丁猛[1] 刘卫东[1] 周进[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：《推进技术》2008年第3期312-317,共6页Journal of Propulsion Technology

基　　金：国家"八六三"项目(2002AA723060)

摘　　要：为了解凹腔火焰稳定器的工作过程,通过试验和数值仿真手段,对超声速条件下凹腔的流动特性进行了深入细致的研究,探讨了气/液喷流与超声速凹腔流动的相互作用机理。研究结果表明,无喷流时超声速凹腔流场具有五个典型的特征;引入喷流会引入新的流场特征,同时流场结构会发生机理性的变化;气/液喷流对凹腔整体流动特征的影响是一致的;有气体喷流时,不同压降下凹腔流场结构是类似的;而对液体喷流而言,提高喷注压降会增加雾化距离、射流穿透度、喷流厚度,提高来流速度则会使其减小。To comprehend the working process of cavity flame holder, characteristics on supersonic flow over cavities were thoroughly investigated by means of experiments and numerical simulations. Interaction between gas/liquid injection and supersonic cavity flow was studied. Results indicate that there are five traits in supersonic cavity flow field without injection; and injection will introduce new traits to the flow field. The structure will alters in mechanism; both gas and liquid injection produce similar effects on the whole cavity flow field; the structures of flow field with gas injection under different pressure drops are homologous ; as for liquid injection, larger pressure drop leads to increase of atomization length, penetration depth, and spray thickness, while enhancing free stream velocity leads to decrease it.

关 键 词：超音速冲压喷气发动机 超音速流动^+ 凹腔^+ 火焰稳定器 数值仿真 

分 类 号：V435.12[航空宇航科学与技术—航空宇航推进理论与工程]