Aircraft power and propulsion system 400, aircraft (500,Fig.7) and methods (600,Fig.8),(700,Fig.9) of starting gas turbine engines (101,Fig.1). Gas turbine engine (101,Fig.1) has first, starting spool and second spool and first and second DC electrical networks 431, 423 having first and second, differing operating voltages. First electrical machine 411 is mechanically coupled with first spool and has first and second winding sets 4111,4112. Second electrical machine 413 is mechanically coupled with the second spool. First and second AC:DC converters 4211,4212 are connected to first and second winding set 4111,4112 respectively on an AC-side and first and second DC electrical networks 431,432 on the DC side. Third AC:DC converter is connected to first DC electrical network 431 on a DC-side and connected to a controllable switching arrangement 441-443 on an AC side so that the connection to an AC-side of the third AC:DC converter 4231 is switchable between winding 4131 of second electrical machine or second DC electrical network 432 via inductor 445,446, which may be transformer 446. Fourth AC:DC converter may connect to second winding set 4132 of second electrical machine 413 on an AC side and to second DC electrical network 432 on a DC side.


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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 :

    25.12.2024


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

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



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