An actuating device of a fuel pump for an aircraft engine includes: a motor, a generator and an electrical connection member, the motor being an asynchronous machine with Dahlander coupling including a first rotor coupled to the pump for actuation thereof, and a first stator including at least one input phase, each input phase comprising two windings, the generator including a second rotor mechanically coupled to a shaft of the engine, and a second stator including at least one output phase, the electrical connection member being configured so as to connect each output phase to an input phase, and to connect the windings of each input phase in series or in parallel according to a speed of the engine.
PUMP ACTUATING DEVICE, AND ASSOCIATED PUMPING SYSTEM, AIRCRAFT AND FUEL SUPPLY METHOD
28.11.2024
Patent
Elektronische Ressource
Englisch
IPC: | H02P CONTROL OR REGULATION OF ELECTRIC MOTORS, ELECTRIC GENERATORS OR DYNAMO-ELECTRIC CONVERTERS , Steuern oder Regeln von elektrischen Motoren, elektrischen Generatoren, dynamoelektrischen Umformern / B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT / F04D Strömungsarbeitsmaschinen , NON-POSITIVE-DISPLACEMENT PUMPS |