超声速燃烧室凹腔构型优化研究进展OA

In air-breathing hypersonic vehicles,scramjet propulsion systems face core challenges such as fast and adequate fuel-supersonic airflow mixing,effective combustion,and robust flame stabilization.As one of the most widely used flame stabilization devices in scramjet combustors,the cavity shows a profound influence on the fuel mix-ing and combustion process,as well as the combustor performance.This paper systematically reviews research prog-ress on the effects of cavity configurations on flow characteristics and combustor performance in supersonic combus-tors.First,a concise overview of the supersonic cavity is introduced,including the basic configurations,the typical flow structures,and physical effects of the supersonic cavity.Second,the influence of fundamental cavity configura-tion parameters,including cavity length,depth,length-to-depth ratio,rear-wall inclination angle,and front-wall inclina-tion angle,on flow and combustion characteristics such as cavity recirculation zone structures,fuel residence time and flame stability is summarized and analyzed.Third,the optimization of two-dimensional cavity configurations is system-atically elaborated on the basis of three physical mechanisms:extension of recirculation zones/vortical structures;re-construction of shock/expansion wave systems;and modulation of shear layer dynamics.Furthermore,three-dimensional cavity optimization is discussed,with a focus on the streamwise vortex enhancement and lateral mass ex-change.Finally,recommendations are proposed for the configuration optimization and design of cavity flameholders,taking into account the current research status and technical bottlenecks.