A hybrid propulsion system (10, 20) for aircrafts comprises at least a fuel cell unit (13) for providing power to drive an aircraft (100) by using hydrogen in a redox reaction, at least a gas turbine (11) for providing power to drive the aircraft (100) by burning hydrogen, a hydrogen source (12) for providing the hydrogen to the fuel cell unit (13) and/or to the gas turbine (11) and at least an electric propulsion unit (14, 24) for driving the aircraft (100). The electric propulsion unit (14, 24) is electrically powered by the fuel cell unit (13) and/or mechanically by the gas turbine (11) in at least two different propulsion modes (M1, M2). A control unit (27) controls the power supply to the electric propulsion unit (14, 24). In a first propulsion mode (M1) for a first flight phase the electric propulsion unit (14, 24) is essentially or only powered by the fuel cell unit (13), and in a second propulsion mode (M2) for a second flight phase the electric propulsion unit (14, 24) is essentially or only powered by the gas turbine (11).
HYBRID PROPULSION SYSTEM FOR AIRCRAFT, METHOD OF OPERATING A HYBRID PROPULSION SYSTEM, AND A HYBRID AIRCRAFT
HYBRIDANTRIEBSSYSTEM FÜR FLUGZEUGE, VERFAHREN ZUM BETRIEB EINES HYBRIDANTRIEBSSYSTEMS UND HYBRIDFLUGZEUG
SYSTÈME DE PROPULSION HYBRIDE POUR AÉRONEFS, PROCÉDÉ DE FONCTIONNEMENT D'UN SYSTÈME DE PROPULSION HYBRIDE ET AÉRONEF HYBRIDE
2021-04-14
Patent
Electronic Resource
English
IPC: | B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT |