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.


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    Title :

    GAS TURBINE ENGINE BLEED CONFIGURATION


    Additional title:

    CONFIGURATION DE PURGE DE MOTEUR DE TURBINE A GAZ


    Contributors:
    MORGAN KEITH (author) / PLANTE GHISLAIN (author) / DUROCHER ERIC S (author) / NG KEVIN (author) / VINSKI JOHNNY (author)

    Publication date :

    2018-05-14


    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



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