Air intake duct for supplying air to a turbine engine gas generator, in particular an aircraft turbine engine, extending axially between the air intake and the gas generator and having a deflection which may cause shedding of the boundary layer formed by the air flow along the wall of the duct, wherein said air intake duct comprises a guiding element located in the duct and designed to guide the air along the wall of the duct to a portion having the deflection, said guiding element extending transversely to the direction of the flow of air and having at the ends thereof two end profiles that form a non-zero angle with the guiding element, said two end profiles being able to produce eddies in the air flow.


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    Titel :

    Aircraft turbine engine air intake duct



    Erscheinungsdatum :

    2019-06-11


    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 / F02K JET-PROPULSION PLANTS , Strahltriebwerke



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