A blade of a gas turbine engine may comprise a cavity defined, at least partially, by a first interior surface of the blade and by a second interior surface of the blade. A first rib and a second rib may extend from the first interior surface. A third rib may extend from the second interior surface and may be located between the first rib and the second rib. A bulkhead rib may traverse the cavity and may separate the cavity into a radially inward portion and a radially outward portion. A viscoelastic material may be disposed in the radially inward portion of the cavity.


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    Titel :

    Blade with damping structures


    Beteiligte:

    Erscheinungsdatum :

    2019-11-05


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    F04D Strömungsarbeitsmaschinen , NON-POSITIVE-DISPLACEMENT PUMPS / 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



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