An air duct interface for an aircraft engine is disclosed herein. The air duct interface includes a first air duct, a first outer wall, a mating interface disposed circumferentially around the first outer wall, a second air duct, a second outer wall, and a gasket interface disposed circumferentially around the second outer wall. The mating interface includes a first angled portion extending away from the first outer wall in a first direction and a second angled portion extending away from the first outer wall in a second direction opposite the first direction. The gasket interface includes a first portion extending away from the second outer wall in the first direction, wherein the first portion is configured to engage the first angled portion and a second portion extending away from the second outer wall in the second direction, wherein the second portion is configured to engage the second angled portion.


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    Titel :

    MECHANISM FOR CONNECTING HIGH TEMPERATURE AIR DUCTING FOR AIRCRAFT ENGINE


    Beteiligte:

    Erscheinungsdatum :

    17.04.2025


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    F24F Klimatisierung , AIR-CONDITIONING / B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT



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