Propulsion assembly for an aircraft, comprising a fuselage extending along a longitudinal axis and enclosing an inner enclosure, at least one ducted engine fixed to the fuselage and comprising an air inlet section, the air inlet section being disposed at least partly in the inner enclosure, at least one plenum chamber disposed in the inner enclosure upstream of the air inlet section and in fluid communication with said air inlet section, at least one air intake formed on an outer wall of the fuselage, the inlet of the air intake being partly delimited by said outer wall of the fuselage, the air intake being configured to ingest external air and deflect it towards the plenum chamber.


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    Titel :

    PROPULSION UNIT WITH IMPROVED BOUNDARY LAYER INGESTION



    Erscheinungsdatum :

    2022-09-01


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    B64C AEROPLANES , Flugzeuge / B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT



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