An aircraft engine, has: an inlet leading to a compressor section, the inlet extending circumferentially around a central axis; an annular inlet duct extending circumferentially around the central axis, the annular inlet duct having a duct inlet fluidly connected to an environment outside of the aircraft engine and a duct outlet fluidly connected to the inlet, the duct outlet extending circumferentially around the central axis; and a flow restrictor located within the annular inlet duct, the flow restrictor extending across the annular inlet duct, being movable within the annular inlet duct along a circumferential direction relative to the central axis in response to a fluid pressure differential on opposed sides of the flow restrictor.


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    Titel :

    AIRCRAFT INTAKE DUCT WITH PASSIVELY MOVABLE FLOW RESTRICTOR


    Weitere Titelangaben:

    CONDUITE D'ENTREE D~AIR D~AERONEF COMPRENANT UN LIMITEUR DE DEBIT PASSIVEMENT MOBILE


    Beteiligte:
    AKCAYOZ ERAY (Autor:in)

    Erscheinungsdatum :

    2024-02-05


    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



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