A gas turbine engine includes a compressor section having a first compressor and a second compressor and a turbine section having a first turbine and a second turbine. The first compressor is connected to the first turbine via a first shaft and the second compressor is connected to the second turbine via a second shaft. A motor connected to the first shaft such that rotational energy generated by the motor is translated to the first shaft. A power distribution system connects the motor to a stored power system including at least one of an energy storage unit and a supplementary power unit. The power distribution system is configured to provide power from the stored power system to the motor.


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    Titel :

    POWER SYSTEM FOR AIRCRAFT PARALLEL HYBRID GAS TURBINE ELECTRIC PROPULSION SYSTEM


    Beteiligte:

    Erscheinungsdatum :

    04.01.2018


    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 / F01D Strömungsmaschinen [Kraft- und Arbeitsmaschinen oder Kraftmaschinen], z.B. Dampfturbinen , NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES



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