A method of bleeding air from a gas turbine engine having a compressor section with a downstream centrifugal compressor is described, which includes bleeding air from a first location upstream of the centrifugal compressor's outlet, when the compressor is operating in a first pressure range, and bleeding air from a second location upstream of the centrifugal compressor's outlet, when the engine is operating in a second pressure range.


    Zugriff

    Download


    Exportieren, teilen und zitieren



    Titel :

    GAS TURBINE ENGINE BLEED CONFIGURATION


    Weitere Titelangaben:

    CONFIGURATION DE PURGE DE MOTEUR DE TURBINE A GAZ


    Beteiligte:
    MORGAN KEITH (Autor:in) / PLANTE GHISLAIN (Autor:in) / DUROCHER ERIC S (Autor:in) / NG KEVIN (Autor:in) / VINSKI JOHNNY (Autor:in)

    Erscheinungsdatum :

    14.05.2018


    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



    GAS TURBINE ENGINE BLEED DUCT

    PEACE RICHARD / GOULDS ROBERT | Europäisches Patentamt | 2020

    Freier Zugriff

    Bleed flow assembly for a gas turbine engine

    MILLER BRANDON WAYNE / HUNTER SCOTT DAVID / MARRINAN PATRICK MICHAEL et al. | Europäisches Patentamt | 2024

    Freier Zugriff

    HYBRID GAS TURBINE ENGINE WITH BLEED SYSTEM IMPROVEMENTS

    WOODS ADAM | Europäisches Patentamt | 2023

    Freier Zugriff

    HYBRID GAS TURBINE ENGINE WITH BLEED SYSTEM IMPROVEMENTS

    WOODS ADAM | Europäisches Patentamt | 2021

    Freier Zugriff

    Hybrid gas turbine engine with bleed system improvements

    WOODS ADAM | Europäisches Patentamt | 2022

    Freier Zugriff