为大幅减小发动机耗油率，降低碳排放，提升飞机续航能力，提出了基于碳氢燃料的燃料电池燃气涡轮航空混合推进系统，通过预重整和高温燃料电池实现碳氢燃料的电化学利用并避免传统氢燃料电池飞机储氢困难、体积能量密度小的问题，另一方面，利用燃气涡轮增加燃料电池功率密度，减小其体积和质量。以MQ-1无人机为匹配对象，通过建立推进系统质量和热力学性能模型，对混合系统进行了部件参数匹配分析。随着燃料利用率减小，燃料电池极化减小，换热器平均换热温差增加，因而混合推进系统质量急剧下降，耗油率大幅上升，该航空混合系统质量与总效率的优化方向相反。随压比增加，燃料电池功率和质量增加幅度较大，导致飞机载油量降低，但在燃料电池电流密度为常数时，对燃料电池和混合系统效率影响较小。设计条件下，混合系统中燃料电池和换热器占据混合系统质量的主要部分，超过70%。相比原型内燃机动力，混合推进系统质量约增加40%，但热效率可提高约111%。此外，混合推进系统可满足飞机在爬升阶段和巡航阶段的功率需求，装备该动力的无人机续航时间可提高97%。

To reduce the specific fuel consumption of the engine， reduce carbon emission， and improve aircraft endurance， this paper proposes a Solid Oxide Fuel Cell （SOFC） gas turbine aviation hybrid propulsion system with hydrocarbon fuel. Hydrocarbon fuel is used through pre-reforming and the SOFC， eliminating the need to carry hydrogen with low volume energy density on the aircraft. Moreover， the power density of the hybrid engine is improved， and its mass and volume are decreased by integrating SOFC with gas turbines. Mass and thermodynamic models are constructed to analyze the performance of the hybrid engine equipped with the MQ-1. As the fuel utilization is decreased， the polarization loss of the SOFC is decreased， and the average temperature difference of the heat exchanger is increased， resulting in a decrease in the mass of the hybrid engine and an increase in the specific fuel consumption. The optimization direction of the system mass is opposed to that of the overall efficiency. As the pressure ratio grows， the power and mass of the SOFC are increased， leading to a decrease in fuel mass. However， the efficiency of the fuel cell and the hybrid system is slightly affected when the current density of the fuel cell remains constant. Under the designed conditions， the mass of the SOFC and heat exchangers accounts for more than 70% of the hybrid engine’s total mass. The mass of the hybrid engine is increased by 40%， and the thermal efficiency of the hybrid engine is improved by 111% compared to that of the internal combustion engine. Furthermore， the hybrid engine can meet the power requirements of the aircraft during both climbing and cruising stages. The endurance of an aircraft equipped with a hybrid engine can improve by 97%.