未来高性能空天动力装置中由于高推重比的要求，使得燃油燃烧的环境温度和压力越来越高并达到超临界状态，因此探索液态碳氢燃料的超临界蒸发和燃烧特性是高性能空天动力研究领域急需解决的关键问题之一。液态碳氢燃料超临界物性的特殊性使得其喷射、蒸发和燃烧过程以及流量的测量方法均与亚临界工况差别很大，常规的蒸发和燃烧模型此时均不再适用。本项目拟以实验研究为主，辅以理论和数值分析，探索液态碳氢燃料的超临界蒸发燃烧特性与控制规律。实验测量液态碳氢燃料在不同超临界工况下的物性参数并发展合适的超临界物性计算方法，在实验基础上探索超临界液态碳氢燃料的流量测量方法，研究单个液滴在超临界环境中的蒸发和燃烧规律，建立超临界液滴蒸发和燃烧的数值模型，并对比研究超临界定容燃烧和定压燃烧的基本特性，为未来先进发动机燃烧室中的燃烧组织和设计提供理论与技术基础。

With the increasing of thrust-weight ratio for high-speed propulsion devices in aeronautics and astronautics in the future, the temperature and pressure of the combustion chamber are becoming higher and higher, approaching supercritical conditions. The research on the characteristics of the supercritical evaporation and combustion of liquid hydrocarbon fuels is considered to be one of the key problems for high-speed propulsion devices. The specificity of the physical parameters for liquid hydrocarbon fuels in supercritical condition makes the processes of spray, evaporation and combustion quite different from those in subcritical condition, and conventional evaporation and combustion models are no longer applicable. Based on experimental study, and combined with theoretical analysis and numerical methods, this project intends to research the characteristics and control rules of the supercritical evaporation and combustion of liquid hydrocarbon fuels. The physical parameters of liquid hydrocarbon fuels in different supercritical conditions will be experimentally measured, and the computational model of physical parameters will be developed. Based on the experimental results, the measuring methods of supercritical mass flow rate and the numerical model of supercritical evaporation and combustion will be proposed. The characteristics of evaporation and combustion of individual fuel droplet in supercritical environment will be studied in detail. Characteristics and fundamentals of supercritical constant-volume combustion and constant-pressure combustion will be comparatively analyzed. All of these could lay a theoretical and technique foundation for combustion organization in the combustors and the design for advanced aero- and astro-engines.