Design Concept for a Hybrid Turbo-Electric Regional Aircraft
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Future regional aircraft will need to achieve a balance between efficiency, sustainability and functionality. Hybrid turbo-electric propulsion (HTEP) is a promising step towards achieving this goal, combining the reliability of conventional gas turbine engines with the advantages of distributed electric power. This study presents the preliminary design of a regional aircraft powered by a hybrid turbo-electric propulsion system. Concept development includeds defining baseline requirements for the aircraft and HTEP and addressing specific challenges related to hybrid propulsion. The analysis focuses on selecting an efficient configuration that ensures performance, safety, and operational reliability under typical flight conditions. The work aims to justify the selection of the aerodynamic layout and perform a comprehensive energy balance assessment in order to support the overall design of a regional hybrid aircraft, based on the results achieved. The research findings imply that hybrid turbo-electric propulsion could be a useful transitional technology en route to fully electric or hydrogen-based aviation systems, helping to achieve the long-term goal of climate-neutral flight.
