An assembly is provided for an aircraft propulsion system. This assembly includes a nacelle inner structure that extends axially along and circumferentially about an axial centerline. The nacelle inner structure includes an internal compartment and a cowl. The internal compartment is configured to house a core of a gas turbine engine. The cowl is configured to form an outer radial periphery of the internal compartment. An aft end portion of the cowl is also configured to form an outer radial periphery of a compartment exhaust to the internal compartment. The aft end portion of the cowl includes a plurality of axial fingers arranged circumferentially about the axial centerline in an array.


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    Titel :

    Passive internal compartment exhaust for an aircraft propulsion system


    Beteiligte:

    Erscheinungsdatum :

    2023-06-27


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT / F01D Strömungsmaschinen [Kraft- und Arbeitsmaschinen oder Kraftmaschinen], z.B. Dampfturbinen , NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES / F02C Gasturbinenanlagen , GAS-TURBINE PLANTS / F02K JET-PROPULSION PLANTS , Strahltriebwerke



    PASSIVE INTERNAL COMPARTMENT EXHAUST FOR AN AIRCRAFT PROPULSION SYSTEM

    SHERMAN BRIAN A | Europäisches Patentamt | 2022

    Freier Zugriff

    PASSIVE INTERNAL COMPARTMENT EXHAUST FOR AN AIRCRAFT PROPULSION SYSTEM

    SHERMAN BRIAN A | Europäisches Patentamt | 2021

    Freier Zugriff