Electrical architecture for an aircraft with thermal/electrical hybrid propulsion, comprising, for each turbine engine:an aeroplane AC electrical network,at least one first electrical machine mechanically coupled to a high-pressure shaft of the turbine engine;at least one second electrical machine mechanically coupled to a low-pressure shaft of the turbine engine;a reversible AC/AC electrical energy conversion module;switch elements; andan electronic system for controlling the conversion module and the switch elements, configured to put the architecture;in at least one so-called “power distribution hybridisation” operating mode corresponding to a first configuration of the switch elements in which the at least one second machine is coupled to the aeroplane network and at least one first machine is coupled to the aeroplane network via the electrical energy conversion module.
ELECTRICAL GENERATION ARCHITECTURE FOR HYBRIDISED TURBOMACHINE
2024-10-03
Patent
Electronic Resource
English
IPC: | B60L PROPULSION OF ELECTRICALLY-PROPELLED VEHICLES , Antrieb von elektrisch angetriebenen Fahrzeugen / B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT / H02J CIRCUIT ARRANGEMENTS OR SYSTEMS FOR SUPPLYING OR DISTRIBUTING ELECTRIC POWER , Schaltungsanordnungen oder Systeme für die Abgabe oder Verteilung elektrischer Leistung |
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