Abstract: In recent years, supersonic civil aircraft have garnered increasing interest for their broad potential applications. However, existing propulsion cycle concepts encounter significant challenges in meeting the performance demands of such aircraft, primarily due to the conflicting requirements of cycle parameters for high and low-speed operations. To address this issue, a novel hybrid propulsion system for supersonic civil aircraft is proposed, incorporating a hybrid turbofan engine that integrates hydrogen, intercooling heat transfer, and high-temperature fuel cells. This propulsion cycle amalgamates the benefits of conventional gas turbines and electric propulsion. The intercooling module mitigates issues related to compressor outlet temperature surpassing limits, while the thermoelectric coupling design alleviates high aerodynamic and thermal loads on engine components during high power demands. Consequently, this design reduces the complexity of hot-end component design and enhances operational flexibility. This study mathematically derives the equilibrium equations for this configuration and delves into the physical underpinnings of the component matching principle using a novel performance model based on nonlinear components for the hybrid propulsion system. Additionally, it explores an optimization approach for key design parameters of the new propulsion system, presenting an optimal overall performance design scheme and performance calculations based on the aforementioned methodologies.

Key words: Hydrogen aviation, Fuel cell, Hybrid propulsion, Supersonic civil power, Overall performance simulation, Matching mechanism analysis