液体燃料在主动冷却通道内的湍流热解结焦是高超发动机运行中的突出问题，针对典型液体燃料开展结焦特性的探索和模型化对于传统或新兴航油组分设计、工况优化、结焦抑制等关键技术的研发具有重要的意义。项目重点针对现有结焦预测方法通用性和指导性不足的研究现状，从液体燃料热化学转化的微观本征规律出发，采用模型构建、数值模拟和实验验证多种研究手段，围绕基于详细壁面反应动力学的非稳态结焦机理、基于湍流直接数值模拟的高精度耦合计算方法、典型碳氢燃料的结焦动力学特性及交互影响机制、微通道内湍流热解反应与结焦的耦合作用规律等科学问题开展研究，构建具有燃料和工况适应性的热解结焦模型和CFD计算方法，通过与近真实条件下典型航油组分和工况热解实验结果的对比、验证和优化，实现对于液体燃料热解结焦能力的准确预测。项目成果可为液体碳氢燃料适航性评价体系的完善和新一代高超发动机冷却结构的优化提供模型和方法学上的支撑。

The turbulent pyrolysis coking of liquid hydrocarbon fuel in the regenerative cooling channel is a serious problem during the running process of modern hypersonic engine. The research and modeling of the coking characteristics for typical liquid hydrocarbon fuels are of great significance for the key technology developments, such as fuel component design, operation condition optimization and coking inhibition, etc. Considering that the current coking prediction methods lack generality and guidance, the following researches will be carried out in this project. Starting from the microscopic and intrinsic studies for the thermochemical conversion of different liquid hydrocarbon fuels, and using the research methods combining the theoretical analysis, numerical modeling and principle experiments, several key contents will be studied, which include: unsteady coking mechanism based on the detailed wall surface reaction kinetics, high-precision coupled calculation method based on direct numerical simulation of turbulent flow, coking characteristics of different liquid hydrocarbon fuels and their interaction mechanisms, coupling effect of turbulent pyrolysis reaction and coking processes in the micro channel. Based on the above researches, the pyrolysis coking model and corresponding calculation method with high fuel adaptability and operation adaptability will be developed. Furthermore, the numerical simulation and prediction of coking characteristics for typical liquid fuels will be performed together with the detailed comparisons against experimental data under the real operation conditions. The fundamental research results in this project can be used to improve the fuel airworthiness evaluation accuracy and provide the optimization design method for the regenerative cooling channel structure of hypersonic engine.