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.


    Access

    Download


    Export, share and cite



    Title :

    Blade with damping structures


    Contributors:

    Publication date :

    2019-11-05


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

    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



    BLADE WITH DAMPING STRUCTURES

    POLLACK THOMAS A | European Patent Office | 2021

    Free access

    Turbomachine blade damping

    Rao, J.S. | Online Contents | 2003


    ARTICULATED ROTOR SYSTEMS WITH BLADE-TO-BLADE DAMPING

    HALDEMAN ANDREW PAUL / HAMPTON DALTON T / STAMPS FRANK BRADLEY | European Patent Office | 2020

    Free access

    Articulated Rotor Systems with Blade-to-Blade Damping

    HALDEMAN ANDREW PAUL / HAMPTON DALTON T / STAMPS FRANK BRADLEY | European Patent Office | 2019

    Free access

    Articulated rotor systems with blade-to-blade damping

    HALDEMAN ANDREW PAUL / HAMPTON DALTON T / STAMPS FRANK BRADLEY | European Patent Office | 2020

    Free access