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.
ARCHITECTURE DE GÉNÉRATION ÉLECTRIQUE POUR TURBOMACHINE HYBRIDÉE
ELECTRICAL GENERATION ARCHITECTURE FOR HYBRID TURBINE ENGINE
STROMERZEUGUNGARCHITEKTUR FÜR HYBRIDTURBINENMOTOR
15.05.2024
Patent
Elektronische Ressource
Französisch
IPC: | B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT / B60L PROPULSION OF ELECTRICALLY-PROPELLED VEHICLES , Antrieb von elektrisch angetriebenen Fahrzeugen / 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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