Air intake sleeve (32) for an aircraft turboprop engine, comprising an air bleed duct (54) that is oriented substantially along a first axis (A) and a duct (56) for supplying air to a compressor, which duct is oriented substantially along a second axis (B), at a distance from the first axis and substantially in parallel with the first axis, said air bleed duct and said supply duct being interconnected by an intermediate duct (60) having a general S shape, when viewed from the side, characterised in that said intermediate duct comprises, on at least one of the walls thereof, means for sucking air into the flow path of the intermediate duct, said suction means (64, 66) being positioned and/or designed to suck a boundary layer of said flow path.


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    Titel :

    AIR INTAKE SLEEVE FOR AN AIRCRAFT TURBOPROP ENGINE



    Erscheinungsdatum :

    05.05.2016


    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 / F01D Strömungsmaschinen [Kraft- und Arbeitsmaschinen oder Kraftmaschinen], z.B. Dampfturbinen , NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES / F04D Strömungsarbeitsmaschinen , NON-POSITIVE-DISPLACEMENT PUMPS



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