An aircraft propulsor 200 includes a nacelle 208, a fan (116, fig 1) and a core plug 218. The nacelle includes a leading edge 210 and a trailing edge 212 downstream of the leading edge defining a duct 214 therein. The fan is received within the duct and is configured to rotate about a rotational axis Y-Y’ and generate a primary fluid flow. The core plug is at least partially received within the nacelle and includes a boundary wall 220 radially inward of the nacelle so that the primary fluid flow from the fan passes between the nacelle and the boundary wall 220. The core plug extends axially beyond the trailing edge of the nacelle relative to the rotational axis (Y-Y’) of the fan. The boundary wall of the core plug includes a flow control feature 226 located downstream of the trailing edge of the nacelle for reducing boundary layer separation of the primary fluid flow. The flow control feature may be slots (228, figure 3), vortex generators (240, figure 5) or jet vortex generators (244, figure 9) located on the boundary wall.


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    Titel :

    Aircraft propulsor


    Beteiligte:

    Erscheinungsdatum :

    2021-12-01


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    B64C AEROPLANES , Flugzeuge / B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT / F02C Gasturbinenanlagen , GAS-TURBINE PLANTS / F02K JET-PROPULSION PLANTS , Strahltriebwerke



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