基于液氢热沉利用的氢能涡轮航空发动机拓扑架构优化OA

Hydrogen turbine aero engines,featuring zero carbon emissions and high power density,are a pivotal focus of research in green aviation.A critical factor for enhancing their performance is the effective utilization of liquid hydro-gen(LH2)as a thermal sink.The optimization of hydrogen turbine aero engine topologies is investigated to maximize the use of LH2's thermal sink capabilities.Three topology models for hydrogen turbine aero engines are developed based on their thermal dissipation requirements.A benefit-compensation analysis framework is then established to evalu-ate these topologies across various flight profiles.Optimization of the topological design yielded an architecture that ex-tended the aircraft's endurance by 8.98%.The feasibility of integrating hydrogen turbine aero engines into a 70-seat re-gional airliner is also examined,accounting for the maturity of hydrogen storage technologies.Results indicate that achieving a hydrogen mass fraction of 24.51%enables this class of aircraft to achieve uncompensated zero-carbon op-eration.It provides critical insights into the design,evaluation,and optimization of hydrogen turbine aero engine sys-tems,contributing to the advancement of sustainable aviation technologies.