A blade (102) of a gas turbine engine may comprise a cavity (134) defined, at least partially, by a first interior surface of the blade (102) and by a second interior surface of the blade (102). A first rib (140) and a second rib (142) 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 (140) and the second rib (142). A bulkhead rib (150) may traverse the cavity (134) and may separate the cavity (134) into a radially inward portion and a radially outward portion. A viscoelastic material may be disposed in the radially inward portion of the cavity (134).


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    Titel :

    BLADE WITH DAMPING STRUCTURES


    Weitere Titelangaben:

    SCHAUFEL MIT DÄMPFUNGSSTRUKTUREN
    LAME COMPORTANT DES STRUCTURES D'AMORTISSEMENT


    Beteiligte:

    Erscheinungsdatum :

    2021-04-21


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    B64C AEROPLANES , Flugzeuge / F01D Strömungsmaschinen [Kraft- und Arbeitsmaschinen oder Kraftmaschinen], z.B. Dampfturbinen , NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES / F04D Strömungsarbeitsmaschinen , NON-POSITIVE-DISPLACEMENT PUMPS



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