论文部分内容阅读
凹腔作为促进燃烧室中燃料与来流混合和稳定燃烧的有效手段之一,其研究已引起人们的广泛关注。采用数值模拟方法,探索了圆形超燃冲压发动机燃烧室阻力特性随凹腔结构参数的变化趋势,同时初步考察了飞行攻角对凹腔阻力特性的影响。研究发现,凹腔摩阻相比压阻很小,凹腔对燃烧室的阻力特性主要体现在其压阻上;随着后掠角的增大,热试和冷流状态下的凹腔阻力均呈现逐渐减小的趋势;随着长深比的增大,热试状态下的凹腔阻力先增加后减小,而冷流状态下的凹腔阻力则单调递减;在小攻角(-3°~3°)热试状态下,燃烧室凹腔阻力明显强于冷流状态下凹腔阻力。这对圆形超燃冲压发动机燃烧室的设计工作具有一定的指导和借鉴意义。
As one of the effective means to promote the mixing and steady combustion of fuel and incoming fuel in the combustion chamber, the research of the cavity has attracted much attention. The numerical simulation method was used to investigate the changing trend of the resistance characteristics of the combustor of a round scramjet with the structural parameters of the cavity. At the same time, the influence of the flight angle on the resistance of the cavity was investigated. The results show that the friction resistance of the cavity is very small compared with that of the cavity. The resistance of the cavity to the combustion chamber is mainly reflected by the piezoresistive resistance. With the increase of the sweep angle, the cavity resistance The resistance of the cavity increases firstly and then decreases with the increase of the aspect ratio, while the resistance of the cavity under the condition of cold flow decreases monotonically. At the small angle of attack (- 3 ° ~ 3 °) thermal test state, the combustion chamber cavity resistance was significantly stronger than the cavity under cold flow resistance. This has certain guidance and reference significance for the design work of a round scramjet engine combustion chamber.