A fan nacelle (34) for a gas turbine engine includes a leading edge region (40) with a flow path (42) between an intake region (48) in a nacelle outer surface (44) and an exhaust region (50) in a nacelle inner surface (46) to locally modify a flow around the leading edge region (40) during a predefined off-design condition.


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    Title :

    Fan nacelle with porous surfaces


    Additional title:

    Gebläse-Gondel mit porösen Flächen
    Nacelle de soufflante dotée de surfaces poreuses


    Contributors:

    Publication date :

    2019-08-14


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

    IPC:    F02C Gasturbinenanlagen , GAS-TURBINE PLANTS / F02K JET-PROPULSION PLANTS , Strahltriebwerke / F01D Strömungsmaschinen [Kraft- und Arbeitsmaschinen oder Kraftmaschinen], z.B. Dampfturbinen , NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES / B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT



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