Flight performance and matching mechanism of a novel hydrogen-powered mixed-flow turbofan hybrid propulsion system

Due to their significant application potential, supersonic civil aircraft have attracted growing research interest. However, existing propulsion cycle architectures face considerable challenges in meeting the performance demands of such aircraft. This study presents a comparative assessment of mission performance between a proposed hydrogen intercooling and recuperating solid oxide fuel cell integrated with a mixed flow turbofan (HIR–SOFC–MTF) and a hydrogen intercooling and recuperating mixed flow turbofan (HIR-MTF). Through analysis of internal matching mechanisms, the underlying causes of performance differences are elucidated, and the operational regime in which the novel engine offers advantages is identified. Results indicate that during a Mach 2 supersonic cruise mission, the aircraft powered by the hybrid engine achieves a 13.38% increase in total range under identical available fuel conditions, attributed to superior installed performance. This advantage stems from enhanced throttling characteristics enabled by integrated regulation through a thermo-electrical coupling cycle.