A vane assembly within a mid-turbine frame of a gas turbine engine includes an airfoil that extends between an outer platform and an inner platform. The airfoil includes an outer wall defining a leading edge of a first radius. An inner wall of the airfoil defines an inner cavity including a forward portion proximate the leading edge defining a second radius different than the first radius.


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    Title :

    Stress mitigation feature for composite airfoil leading edge


    Contributors:

    Publication date :

    2019-11-26


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

    IPC:    F04D Strömungsarbeitsmaschinen , NON-POSITIVE-DISPLACEMENT PUMPS / B63H Schiffsantrieb oder Steuerung der Schiffe , MARINE PROPULSION OR STEERING / B64C AEROPLANES , Flugzeuge / F01D Strömungsmaschinen [Kraft- und Arbeitsmaschinen oder Kraftmaschinen], z.B. Dampfturbinen , NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES / F03B MACHINES OR ENGINES FOR LIQUIDS , Kraft- und Arbeitsmaschinen oder Kraftmaschinen für Flüssigkeiten / F03D Windkraftmaschinen , WIND MOTORS



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