A nacelle (12) for a gas turbine jet engine (10) for an aircraft (18) includes plasma actuators (42) that act as flow disruptors to provide boundary layer turbulence when the engine (10) is exposed to air flow that is obtuse or perpendicular to direction of travel of the engine.


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    Title :

    ENGINE NACELLE


    Additional title:

    TRIEBWERKSGONDEL
    NACELLE DE MOTEUR


    Contributors:

    Publication date :

    2018-10-03


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

    IPC:    B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT / B64C AEROPLANES , Flugzeuge / F01D Strömungsmaschinen [Kraft- und Arbeitsmaschinen oder Kraftmaschinen], z.B. Dampfturbinen , NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES / F02K JET-PROPULSION PLANTS , Strahltriebwerke / F15D FLUID DYNAMICS, i.e. METHODS OR MEANS FOR INFLUENCING THE FLOW OF GASES OR LIQUIDS , Strömungsdynamik, d.h. Verfahren oder Vorrichtungen zum Beeinflussen der Strömung von Gasen oder Flüssigkeiten



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