A turbine component (200) includes an airfoil (206, 1700) extending between an inner platform (202) and an outer platform (204), a leading edge rib (412) positioned in a leading edge region (406) of the airfoil (206, 1700) and having a plurality of leading edge rib openings (424), each leading edge rib opening (424) positioned nearer to one of a pressure side wall (208) and a suction side wall (210) of the airfoil (206, 1700) than the other of the pressure side wall (208) and the suction side wall (210), a rear rib (404) positioned in a trailing edge region (410) of the airfoil (206, 1700), a first cooling path (702) extending from a flow inlet (504, 508, 1802) formed in one of the inner platform (202) and the outer platform (204), through the leading edge region (406), through an inner platform cooling passage (514), and into the trailing edge region (410), and a second cooling path (704) extending from the flow inlet (504, 508, 1802), through a middle region (408) of the airfoil (206, 1700), and into the trailing edge region (410).


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    Titel :

    Turbine component for gas turbine engine


    Erscheinungsdatum :

    18.10.2023


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch



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