A gas turbine engine augmentor includes an augmentor outer casing (502) and an annular augmentor liner (504) disposed radially within and radially separated from the augmentor outer casing (502) to form a generally annular augmentor liner cooling flow path (500) between the augmentor casing and the annular augmentor liner, and an augmentor flow splitter duct (506) disposed at the upstream end of the augmentor liner and radially between the augmentor outer casing (502) and the annular augmentor liner (504) and defining a splitter flow path (520) between the annular augmentor liner (504) and the annular augmentor flow splitter duct (506). A method of operating a gas turbofan engine including an augmentor includes directing a portion of fan bypass air into a generally annular augmentor liner cooling flow path (500) between an augmentor outer casing (502) and an annular augmentor liner (504), directing a portion of the air in the augmentor liner cooling flow path (500) into a splitter flow path (520) disposed radially outside the augmentor liner (504) and maintaining positive backflow pressure margin between air flow within the splitter flow path and the augmentor liner cooling flow path (500).


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    Titel :

    Exhaust duct flow splitter system


    Weitere Titelangaben:

    System zur Abgaskanalströmungsspaltung
    Système séparateur de flux de conduit d'échappement


    Beteiligte:

    Erscheinungsdatum :

    2017-04-19


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT / F02K JET-PROPULSION PLANTS , Strahltriebwerke



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