An air inlet duct (18, figure 1), in particular for an aircraft turbine engine comprising a gas generator, extends axially between the air inlet (10, figure 1) and the gas generator and has a first axial wall part 18A and a second wall part 18D which is angularly offset with respect to the first part 18A. The second wall part 18D of the duct 18 is capable of causing, in a shedding region, shedding of the boundary layer formed by an air flow along the wall of the duct. A device for controlling said shedding of the boundary layer comprises an air-blowing pipe 22,24 which opens via at least one air-injection opening which is directly upstream of the shedding region. The blowing pipe 22,24 is connected to an air intake positioned upstream of said air-injection opening or in the shedding region. An air compressor 26 is provided between the air intake and the air-injection opening.


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    Titel :

    Air inlet duct for an aircraft turbine engine


    Beteiligte:

    Erscheinungsdatum :

    08.11.2017


    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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