A rotor for an aircraft engine, has: a hub extending circumferentially about a central axis, the hub having a bore, a gaspath-facing surface located radially outwardly of the bore relative to the central axis, a first face extending from the bore to the gaspath-facing surface, and a second face opposite the first face and extending from the bore to the gaspath-facing surface; blades circumferentially distributed about the central axis, the blades protruding away from the gaspath-facing surface of the hub; and a crack mitigator located on the first face, the crack mitigator extending circumferentially relative to the central axis, the crack mitigator extending axially from a baseline surface of the first face.


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    Title :

    ROTOR HAVING CRACK MITIGATOR


    Additional title:

    ROTOR COMPRENANT UN ATTENUATEUR DE FISSURES


    Contributors:

    Publication date :

    2023-10-08


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

    IPC:    F02C Gasturbinenanlagen , GAS-TURBINE PLANTS / B23P Sonstige Metallbearbeitung , OTHER WORKING OF METAL / B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT / F01D Strömungsmaschinen [Kraft- und Arbeitsmaschinen oder Kraftmaschinen], z.B. Dampfturbinen , NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES



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