随着战斗机性能不断提升，热环境越发严峻，燃油综合热管理系统成为保障热安全性的关键，故高性能热管理系统的研究具有重要意义。燃油循环流路是航空发动机的重要组成部分，其部件众多、流路复杂，增加了热管理系统建模仿真和性能优化的难度。因此，本文针对航空发动机燃油综合热管理系统，设计模拟实验系统，研究主要部件的流动与换热模型，以及稳态与瞬态工况下系统的流动与换热特性。 论文首先确定了先进热管理系统的设计方向，提出包含复杂航空发动机燃-滑油系统的原理框架。结合工程实际和实验室条件，设计安全可行的模拟实验系统，满足部件特性测试和飞行特性模拟实验的需求。参照F-22的飞行状态参数，缩比确定了实验系统的标准工况参数，选择了合适的实验设备，设计出了紧凑的实验装置，并完成了加工与测试。 其次，针对阀门、圆管、齿轮泵、管壳式换热器等部件开展了流动与换热特性实验，获得了多影响因素下的部件特性实验数据，并使用数学模型构建经验关联式或优化仿真算法。结果表明：对于大多数部件，类反比函数模型能够描述阻力系数与雷诺数的关系；对于附加固体结构问题，提出了附加热容模型，能够实现高精度的圆管瞬态换热仿真算法，使数值仿真误差不超过2%；齿轮泵泄漏系数并非定值，而是受间隙热膨胀的影响，基于实验数据训练得到了容积效率的神经网络模型，使用该模型分析了相关的影响因素和规律，整理出了新的预测容积效率的经验关联式；通过实验标定出了螺旋管壳式换热器的阻力系数与换热关联式，确认了其壳侧努谢尔数仍满足幂函数模型。 最后，利用燃油综合热管理模拟实验台，开展了稳态及瞬态的燃油热管理飞行模拟实验，研究了系统的流量调控分配规律和温度控制策略，探讨了热回油方案的作用机理及规律。提出可以基于供油量-阻力系数线性关系设计计量活门结构，以提高供油调控精度；为提高供油稳定性，需要考虑热回油方案对系统流量和压力的影响，优化活门控制策略；通过开式系统瞬态模拟实验，分析了全任务阶段的热沉利用状况，指出仅在供油温度接近限制值时进行热回油才能达到正收益。热回油方案能够显著提升热管理系统的热耐久性，是提高燃油热沉利用率的重要策略。

An increasingly severe thermal environment appears as the improvement of fighter performance and the integrated fuel thermal management system has become the key issue ensuring thermal safety, which makes the research on high-performance thermal management systems of great significance. The fuel cycle circuit is an important part of aeroengine, with numerous components and complex flow paths, which increases the difficulty in its modeling, simulation, and performance optimization for thermal management. Therefore, this thesis aims at designing an experimental simulation system of integrated fuel thermal management for aeroengine, investigating the flow and heat transfer models of the major components in the integrated fuel heat management system, and studying the flow and heat transfer characteristics of the system under steady-state and transient conditions. Firstly, the design direction of an advanced fuel thermal management system was determined, and a principle framework including complex aeroengine fuel-lubrication oil system was proposed. Combined with engineering practice and laboratory conditions, a safe and feasible simulation experiment system was designed to meet the requirements of component characteristic test and flight characteristic simulation experiment. The standard operating parameters of the experimental system were determined by refering to F-22 flight status parameters with reduced scale. Appropriate experimental equipments were selected. A compact experimental system for integrated fuel thermal management was designed, assembled and debugged. Secondly, empirical formulas or optimization simulation algorithms of flow and heat transfer of components such as valves, circular tubes, gear pumps, and shell-and-tube heat exchangers were obtained based on experimental data. The results show that the inverse function model can describe the relationship between resistance coefficient and Reynolds number for most components. An extras heat capacity method that describes the transient heat transfer of circular tubes with attached structures was proposed. It can optimize the transient heat transfer simulation algorithm and reduced simulation error of transient temperature below 2%. It was found that the leakage coefficient of the gear pump is not a constant value and the leakage was affected by the gap’s thermal expansion. A neural network model of volumetric efficiency was obtained based on the experimental data training, which is used to analyze the relevant influencing factors and rules, and sort out a new empirical correlation formula for predicting volumetric efficiency. For the spiral tube-and-shell heat exchangers, the shell side Nusselt number still satisfied the power function model. Finally, steady-state and transient flight simulation experiments were conducted to study the flow regulation and distribution and temperature control strategies of the system, and to explore the mechanism and engineering implementation methods of the hot fuel return scheme. It is proposed that the metering valve structure can be designed based on the linear relationship between fuel flow supply and resistance coefficient to improve the precision of fuel supply control. It is necessary to consider the impact of hot fuel return scheme on system flow rate and pressure, and optimize the valve control strategy. The results on the open fuel loop show that the hot fuel return scheme can significantly improve the thermal durability of the thermal management system, and is also an important strategy to improve the utilization rate of the fuel heat sink. However, only when the fuel supply temperature approaches the limit value can a positive return be achieved by performing a hot fuel return.