A fan for a gas turbine engine comprises blades distributed around a hub. The blades include first and second blades, having geometric parameters and/or material properties that differ from each other to frequency mistune the fan. The blades are distributed about the hub with at least one second blade between adjacent first blades. The leading edge of the airfoil of the second blades is disposed axially aft of the corresponding leading edge of the first blades in at least a portion of the blade span.


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    Titel :

    Mistuned fan for gas turbine engine


    Beteiligte:
    VEITCH THOMAS (Autor:in) / ABRARI FARID (Autor:in) / ADIQUE ERNEST (Autor:in) / FUDGE DANIEL (Autor:in) / HEIKURINEN KARI (Autor:in) / STONE PAUL (Autor:in) / THERATIL IGNATIUS (Autor:in) / TOWNSEND PETER (Autor:in) / URAC TIBOR (Autor:in)

    Erscheinungsdatum :

    17.11.2020


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    B63H Schiffsantrieb oder Steuerung der Schiffe , MARINE PROPULSION OR STEERING / 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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