A gas turbine engine for an aircraft comprises, in axial flow sequence, a compressor module, a combustor module, and a turbine module. The gas turbine engine further comprises a first electric machine that is rotationally connected to the turbine module, and an electrical energy storage unit. The gas turbine engine is configured to generate a maximum dry thrust T (N). The first electric machine is configured to generate a maximum electrical power PEM1 (W). The electrical energy storage unit has an energy storage capacity E (Wh), a maximum charge rate C (h-1), and a maximum discharge rate D (h-1). The electrical energy storage unit is configured to store electrical energy that may be generated by the first electric machine.


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    Titel :

    AN IMPROVED GAS TURBINE ENGINE


    Weitere Titelangaben:

    VERBESSERTER GASTURBINENMOTOR
    MOTEUR À TURBINE À GAZ AMÉLIORÉE


    Beteiligte:
    DAVIES PAUL (Autor:in) / MOORE GARETH (Autor:in) / HUSBAND STEPHEN (Autor:in) / TRAINER DAVID (Autor:in) / SCOTHERN DAVID (Autor:in) / GEORGE LUKE (Autor:in)

    Erscheinungsdatum :

    2023-03-15


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    F02K JET-PROPULSION PLANTS , Strahltriebwerke / B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT / F02C Gasturbinenanlagen , GAS-TURBINE PLANTS



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