煤油高氧燃比跨临界湍流燃烧具有混合极不均匀性、物性跃变性和局部低温燃烧等特点，其着火、火焰传播和稳定性问题变得尤为突出，已成为发展高性能航空航天发动机必须突破的关键科学难题之一。目前，国内外关于煤油高氧燃比跨临界湍流燃烧的基础研究较少，本课题以煤油高氧燃比跨临界湍流燃烧特性为研究目标，利用同步高速纹影成像和高速OH化学光成像、动态压力监测和数模理论分析相结合方法，研究煤油跨临界射流雾化破碎形态/蒸发特性以及湍流燃烧火焰结构特征，建立射流动力学参数（韦伯数和动量流率比）和煤油射流温度与火焰结构特征参数（射流核心当量长度、火焰锚定相对位置及火焰传播角）的关系图谱，探索煤油跨临界湍流燃烧着火延迟和燃烧稳定关键控制机制，揭示煤油高氧燃比跨临界燃烧湍流扩散和组分复杂的煤油碳氢大分子低温燃烧化学反应动力学耦合控制燃烧的本质，从试验和理论方面为煤油跨临界湍流燃烧技术发展提供重要的基础试验数据和理论支持。

Kerosene transcritical turbulent combustion with high oxygen-fuel ratio in aerospace engine has the features of extreme mixing inhomogeneity, physical property mutation and low-temperature combustion, and the problems of its ignition, flame propagation and stability become particularly prominent, this has become one of the key scientific issues, and it must be broken through for the development of advanced aerospace engine. At home and abroad, the fundamental research of kerosene transcritical turbulent combustion with high oxygen-fuel ratio is little. The research objective of the project is to explore kerosene transcritical turbulent combustion characteristics. Using synchronous speed schlieren imaging, high-speed OH chemical light imaging, dynamic digital pressure monitoring, numerical modeling, the research of kerosene jet spray atomization, evaporation and turbulent flame structure is performed; the relationship of jet kinetic parameters (Weber number, momentum flow ratio, kerosene temperature) and flame structural characteristics (equivalent length of the jet core, the relative position of the anchor flame and flame propagation angle) is established; the interaction of turbulent diffusion and chemical reaction is explored; ignition delay of kerosene transcritical turbulent combustion is analyzed; the flame stabilization mechanism is provided. The project research provides the important basic data and theoretical support from experimental and theoretical aspects for the technology development of kerosene transcritical turbulent combustion with high oxygen-fuel ratio.