An architecture for powering systems on an aircraft has a gas turbine engine including a main compressor, a combustor, and a turbine. The turbine powers the main compressor, and further powers a propulsor. The turbine is operably connected to drive a generator. The generator is connected to store generated power at a battery. 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 and a tap 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 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.


    Access

    Download


    Export, share and cite



    Title :

    Hybrid gas turbine engine with bleed system improvements


    Contributors:
    WOODS ADAM (author)

    Publication date :

    2022-08-23


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

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



    HYBRID GAS TURBINE ENGINE WITH BLEED SYSTEM IMPROVEMENTS

    WOODS ADAM | European Patent Office | 2023

    Free access

    HYBRID GAS TURBINE ENGINE WITH BLEED SYSTEM IMPROVEMENTS

    WOODS ADAM | European Patent Office | 2021

    Free access

    GAS TURBINE ENGINE BLEED DUCT

    PEACE RICHARD / GOULDS ROBERT | European Patent Office | 2020

    Free access

    GAS TURBINE ENGINE BLEED CONFIGURATION

    MORGAN KEITH / PLANTE GHISLAIN / DUROCHER ERIC S et al. | European Patent Office | 2018

    Free access

    Engine bleed system with multi-tap bleed array

    SCHWARZ FREDERICK M | European Patent Office | 2020

    Free access