An architecture for powering systems on an aircraft has a gas turbine engine (22) including a main compressor, a combustor, and a turbine. The turbine powers the main compressor, and further powers a propulsor (24). The turbine is operably connected to drive a generator (26). The generator is connected to store generated power at a battery (28). The battery is connected to provide power to a motor from the propulsor such that the propulsor can be selectively driven by both the motor and the turbine. A bleed air control system (36) and a tap (34) for selectively tapping compressed air from the main compressor, and a control valve for delivering at least one of the tapped compressed air or a compressed alternative air to bleed systems on an associated aircraft. An electric bleed compressor (42) selectively compresses the compressed alternative air. The electric bleed compressor is powered by the battery. A control for controlling the control valve to selectively deliver at least one of the tapped compressed air and the compressed alternative air to the bleed systems. An aircraft is also disclosed.


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    Titel :

    HYBRID GAS TURBINE ENGINE WITH BLEED SYSTEM IMPROVEMENTS


    Weitere Titelangaben:

    HYBRIDGASTURBINENMOTOR MIT VERBESSERUNGEN DES ZAPFLUFTSYSTEMS
    MOTEUR À TURBINE À GAZ HYBRIDE DE PURGE PRÉSENTANT DES AMÉLIORATIONS DU SYSTÈME DE PURGE


    Beteiligte:
    WOODS ADAM (Autor:in)

    Erscheinungsdatum :

    2023-11-08


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

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



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