A hybrid electric gas turbine propulsion system (100) may comprise: a first propulsion system (401), a second propulsion system (402), and a third propulsion system (403). The first propulsion system (401) may comprise a first fan (212), a first turbine (252), a first compressor (232), and a first electric motor (190), the first fan (212) operably coupled to the first turbine (252) and the first compressor (232) by a first shaft (126), the first shaft (126) coupled to the first electric motor (190), the first shaft (126) configured to be disposed radially inward of a fuselage (12) of an aircraft (10). The second propulsion system (402) and the third propulsion system (403) may be in accordance with the first propulsion system (401). The hybrid electric gas turbine propulsion system (100) may be symmetric about a vertical plane extending through a neutral aerodynamic axis (104).


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    Title :

    SYSTEMS AND METHODS FOR GAS TURBINE ENGINES


    Additional title:

    SYSTEME UND VERFAHREN FÜR GASTURBINENMOTOREN
    SYSTÈMES ET PROCÉDÉS POUR MOTEURS À TURBINE À GAZ


    Contributors:

    Publication date :

    2025-08-06


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

    IPC:    B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT



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