Aircraft power and propulsion systems 400 and methods 600, 700 of starting gas turbine engines 101 of aircraft power and propulsion systems 400 are disclosed. In one example, an aircraft power and propulsion system 400 comprises a gas turbine engine 101 having a first and second spools, the first spool being a designated starting spool; first and second DC electrical networks 431, 423 having first and second operating voltages; a first electrical machine 411 mechanically coupled with the first spool, the first electrical machine 411 having a first winding set 4111 and a second winding set 4112; a second electrical machine 413 mechanically coupled with the second spool; a first AC:DC converter, an AC-side of which is connected to the first winding set 4111 of the first electrical machine 411, and a DC-side of which is connected to the first DC electrical network 431; a second AC:DC converter 4212, an AC-side of which is connected to the second winding set 4112 of the first electrical machine 411, and a DC-side of which is connected to the second DC electrical network 432; a third AC:DC converter, a DC-side of which is connected to the first DC electrical network 431; and a controllable switching arrangement 441-443 configured so that a connection to an AC-side of the third AC:DC converter 4231 is switchable between: a winding 4131 of the second electrical machine; or the second DC electrical network 432 via an inductor 445, 446.


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    Titel :

    Electrically starting a gas turbine engine


    Beteiligte:
    DAVID R TRAINER (Autor:in) / MARK SWEET (Autor:in) / MATTHEW S CARTWRIGHT (Autor:in)

    Erscheinungsdatum :

    30.07.2025


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    F02C Gasturbinenanlagen , GAS-TURBINE PLANTS / H02K Dynamoelektrische Maschinen , DYNAMO-ELECTRIC MACHINES / B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT



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