旋转爆震动力与推进技术是促进空天飞行发展的前沿热点技术。旋转爆震的燃烧特性与调控机制的研究对于旋转爆震发动机的工程实践十分重要。本文针对两相旋转爆震燃烧过程开展数值模拟和实验测试的研究工作，旨在揭示两相旋转爆震燃烧组织机理以及稳定燃烧调控机制。首先，基于煤油/富氧空气旋转爆震燃烧室三维冷流场的数值研究，探索完全雾化蒸发的煤油气与富氧空气在旋转爆震燃烧室的掺混行为，分析冷流喷注掺混阶段的流场演化过程，并且开展流动物理机理研究。设计了位于燃烧室壁面的不同类型的凹腔结构，探究该结构及其几何参数对掺混特性的影响，发现壁面凹腔内部产生流体涡旋并提高湍动能，并且后缘处存在低速回流区增强流体卷吸作用，从而增进了煤油气与富氧空气的掺混。其次，采用高频压力传感器获取燃烧室壁面处的压力信号，针对带有壁面凹腔结构的环形旋转爆震燃烧室开展实验研究，分析了流量、当量比和壁面凹腔结构及其位置参数等变量对煤油/富氧空气旋转爆震燃烧的模态分布、爆震波速、爆震波传播位置、起爆及熄爆过程等燃烧特性的影响。研究发现，内凹腔燃烧室可以显著拓展单波爆震模态的稳定形成区间，而外凹腔燃烧室则缩小该稳定形成区间。此外，内凹腔结构可以提升单波爆震模态的爆震波速并降低波速波动率。并且，实验发现随着轴向距离的减小，该影响逐渐增强。最后，针对带有典型壁面凹腔结构的透明旋转爆震燃烧室开展两相旋转爆震流场结构的高速摄像可视化实验研究，采用图像处理算法获得CH*化学发光强度分布，讨论了两相旋转爆震波面的稳定传播过程、起爆过程、熄爆过程。针对典型模态的单波爆震模态、双波对撞爆震模态稳定传播阶段的流场发展过程进行深入分析。此外，针对单波爆震模态的起爆及熄爆阶段的流场发展过程开展研究，建立其起爆及熄爆阶段的全过程传播模型，探究两相旋转爆震燃烧特性。
Rotating detonation propulsion and technology are currently leading the way in aerospace flight development. It is essential to comprehend the combustion characteristics and control mechanisms of rotating detonation for the practical implementation of rotating detonation engines. This study conducts numerical simulations and experimental tests on two-phase rotating detonation combustion, aiming to reveal the organizational mechanism and stability control mechanisms of this process.Firstly, numerical research of the three-dimensional cold flow field in a kerosene/oxygen-enriched air rotating detonation combustor was conducted to analyze the mixing behavior of fully atomized and evaporated kerosene gas with oxygen-enriched air in a rotating detonation combustor. The research focused on the cold flow field evolution during injection and mixing stages, investigating fluid dynamics mechanisms. Different types of cavities were designed and their influence on mixing characteristics was explored. Inner wall cavities were found to generate fluid vortices and enhance turbulent kinetic energy. Furthermore, a low-speed recirculation region at the trailing edge of cavity was identified, which strengthens fluid entrainment and promotes kerosene and air mixing.Furthermore, a study investigated an annular rotating detonation combustor with wall cavity structures using high-frequency pressure sensors to collect wall pressure signals. The analysis examined the impact of variables such as flow rate, equivalence ratio, wall cavity structure and its location parameters on combustion mode distribution, rotating detonation wave velocity and its fluctuation rate, rotating detonation wave propagation location, ignition and extinction processes in kerosene/oxygen-enriched air rotating detonation combustion. Results suggest that the inner-cavity in the combustor can expand the stable formation range of single-wave detonation mode, while outer-cavity reduces this range. Furthermore, inner-cavity structure can enhance detonation wave velocity and decrease the wave velocity fluctuation rate of single-wave detonation mode, with a stronger influence observed as the axial distance decreases.Lastly, a high-speed camera visualization experiment was conducted on a transparent rotating detonation combustor with typical wall cavity structures to investigate the structure of the two-phase rotating detonation flow field. Image processing methods were used to analyze the CH* chemiluminescence intensity distribution, and the study delved into the stable propagation process, ignition process and extinction process of the two-phase rotating detonation waves. The research included an in-depth analysis of the flow field development process during the stable propagation stage of typical combustion modes, such as the single-wave detonation mode and counter-rotating two-wave detonation mode. Furthermore, the study examined the flow field development process during the ignition and extinction stages of the single-wave detonation mode operating conditions. A comprehensive propagation model was established for the entire ignition and extinction stages to explore the characteristics of two-phase rotating detonation combustion.
