航空电气化对机载电源系统的功率密度与运行效率提出了更高的要求，传统辅助动力装置目前正面临效率与排放的双重瓶颈。本文提出了一种基于液氢间冷回热与级间引气耦合的航空燃料电池-燃气轮机机载发电系统，旨在解决传统航空辅助动力装置效率与排放的双重瓶颈。本研究的核心创新在于：通过主发动机压气机级间引气替代了能耗巨大的独立高压空压机；同时，创新性地利用液氢冷能对高温引气进行间冷降温，并回收尾气涡轮余热对氢气进行回热升温。燃料电池尾气经催化燃烧后推动涡轮做功发电，实现了压力能与未反应化学能的梯级回收。研究通过分段压缩功计算法精确评估了引气代偿损失，并重点分析了关键参数对系统净收益的影响。优化结果表明：在典型工况下（引气压比7.25，电堆温度80 °C，匹配最佳电流密度、燃料利用率和过量空气系数），系统总发电功率由初始设计的 40.61 kW 提升至 61.31 kW，系统净收益（净发电功率扣除推进功率损失）由 14.38 kW 增至 32.19 kW，增幅高达 123.8%，整体发电效率达到 55.94%。由此可见，该机载引气耦合方案具备一定的性能优势，为氢能航空混合动力系统的设计提供了理论依据。

Aircraft electrification has raised higher requirements for the power density and operational efficiency of the onboard power system. The traditional auxiliary power unit is currently facing dual bottlenecks of efficiency and emissions. This paper proposes an airborne hybrid power generation system based on liquid hydrogen inter-cooling regenerative heat and inter-stage air introduction coupling for an aerospace fuel cell-gas turbine. The aim is to address the dual bottlenecks of efficiency and emissions in traditional aerospace auxiliary power units. The core innovation of this study lies in: replacing the energy-consuming independent high-pressure air compressor with inter-stage air introduction from the main engine compressor; at the same time, innovatively using liquid hy-drogen cooling energy to inter-cool the high-temperature air and recovering the exhaust turbine residual heat to reheat the hydrogen. The exhaust gas from the fuel cell is catalytically combusted to drive the turbine, achieving stepwise recovery of pressure energy and unreacted chemical energy. The study precisely evaluated the air com-pensation loss using the segmented compression work calculation method and focused on analyzing the impact of key parameters on the system's net benefit. The optimization results show that under typical conditions (exhaust pressure ratio of 7.25, cell temperature of 80 °C, matching the optimal current density, fuel utilization rate and ex-cess air coefficient), the total power generation of the system increases from the initial design of 40.61 kW to 61.31 kW, and the system's net benefit (net power generation minus propulsion power loss) increases from 14.38 kW to 32.19 kW, an increase of 123.8%, and the overall power generation efficiency reaches 55.94%. Thus, this airborne air coupling scheme has certain performance advantages and provides a theoretical basis for the design of hydro-gen-based aerospace hybrid power systems.