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目的:探索壁面凹腔诱导下的超声速混合增强机理,期望得到混合性能较好的燃料喷注策略。方法:提出两种壁面凹腔与横向射流的组合方式,采用数值模拟方法对其流场进行研究,并与纯横向射流流场细节进行对比。结论:1.由于凹腔上面剪切层与壁面横向射流的强烈交互作用,使得横向射流流场中产生的涡系结构被打破;相应地,当把凹腔置于喷孔上游时,亚声速区域面积更大;2.当把凹腔置于喷孔上游时,燃料的渗透深度更大,这样有利于超声速气流中燃料与空气的混合;3.新构型I的混合效率最高。凹腔上面剪切层与壁面横向射流之间的强烈交互作用对超声速气流中燃料的混合增强影响很大,这是超燃冲压发动机燃烧室构型优化的基石。
Objective: To explore the supersonic mixing enhancement mechanism induced by wall cavities, and expect the fuel injection strategy with better mixing performance. Methods: The combination of two kinds of wall cavities and transverse jets was proposed. The flow field was studied by numerical simulation and compared with the details of pure horizontal jet flow field. Conclusions: 1. The vortex structure in the transverse jet flow field is broken due to the strong interaction between the shear layer and the lateral jet in the cavity above the cavity. Correspondingly, when the cavity is placed upstream of the jet hole, 2. When the cavity is placed upstream of the injection hole, the penetration depth of the fuel is greater, which facilitates the mixing of fuel and air in the supersonic airflow. 3. The new configuration I has the highest mixing efficiency. The strong interaction between the shear layer above the cavity and the lateral jet of the wall greatly affects the mixing of the fuel in the supersonic flow, which is the cornerstone of the combustion chamber configuration optimization of the scramjet.