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    HOT GAS PATH COMPONENTS INCLUDING AFT END EXHAUST CONDUITS AND AFT END FLANGES
    1.
    发明申请
    HOT GAS PATH COMPONENTS INCLUDING AFT END EXHAUST CONDUITS AND AFT END FLANGES 有权

    公开(公告)号：US20210246829A1

    公开(公告)日：2021-08-12

    申请号：US16786250

    申请日：2020-02-10

    Applicant: General Electric Company

    Inventor： Jason Ray Gregg ,  Christopher William Kester ,  Christopher Paul Cox ,  David Martin Johnson ,  Ibrahim Sezer

    IPC: F02C7/18 ,  F01D25/12

    Abstract: A turbine shroud for turbine systems may include a forward end including a first hook coupled to the turbine casing, an aft end including a second hook coupled to the turbine casing, and a base portion extending between the forward end and the aft end. The base portion may include an inner surface facing a hot gas flow path for the turbine system. Also, the turbine shroud may include a flange extending from the aft end and positioned radially between the base portion and the second hook, a cooling passage positioned within the base portion, adjacent the inner surface, and at least one aft end exhaust conduit in fluid communication with the cooling passage. The aft end exhaust conduit(s) may extend through the aft end, radially between the base portion and the flange.

    INTERIOR COOLING CONFIGURATIONS IN TURBINE BLADES AND METHODS OF MANUFACTURE RELATING THERETO
    6.
    发明申请
    INTERIOR COOLING CONFIGURATIONS IN TURBINE BLADES AND METHODS OF MANUFACTURE RELATING THERETO 审中-公开

    公开(公告)号：US20190032496A1

    公开(公告)日：2019-01-31

    申请号：US15663228

    申请日：2017-07-28

    Applicant: General Electric Company

    Inventor： Christopher William Kester

    IPC: F01D5/18

    Abstract: A rotor blade for use in combustion turbine engine. The rotor blade may include: an airfoil assembled from two radially stacked non-integral sections in which a body section resides inboard of a cap section; an outboard tip of the airfoil that is enclosed by a tip plate having a tip rail; and a cooling configuration that includes cooling channels for directing a coolant through the rotor blade. Each of the cooling channels may include segments, in which: a supply segment extends radially through the airfoil, the supply segment being radially defined between a floor and ceiling; a rail segment extends through an interior of the tip rail; and a connecting segment extends between the supply segment and rail segment. For each of the one or more cooling channels, the ceiling of the supply segment may be defined within the cap section of the airfoil.

    TURBINE BUCKET HAVING NON-AXISYMMETRIC BASE CONTOUR
    7.
    发明申请
    TURBINE BUCKET HAVING NON-AXISYMMETRIC BASE CONTOUR 有权
    具有非轴对称基座轮廓的涡轮机

    公开(公告)号：US20150110629A1

    公开(公告)日：2015-04-23

    申请号：US14061221

    申请日：2013-10-23

    Applicant: General Electric Company

    Inventor： Lee Larned Brozyna ,  Matthew Durham Collier ,  Christopher William Kester ,  Alexander Stein

    IPC: F01D5/14 ,  F01D5/22 ,  F01D1/04

    CPC classification number: F01D5/141 ,  F01D5/143 ,  F05D2250/74 ,  Y02E20/16 ,  Y02T50/673

    Abstract: Various embodiments of the invention include turbine buckets and systems employing such buckets. Various particular embodiments include a turbine bucket having: an airfoil having: a suction side; a pressure side opposing the suction side; a leading edge spanning between the pressure side and the suction side; and a trailing edge opposing the leading edge and spanning between the pressure side and the suction side; and a base connected with a first end of the airfoil along the suction side, pressure side, trailing edge and the leading edge, the base including a non-axisymmetric contour proximate a junction between the base and the airfoil.

    Abstract translation: 本发明的各种实施例包括涡轮机桶和采用这种铲斗的系统。 各种具体实施例包括涡轮机桶，其具有：具有吸力侧的翼型件; 与吸力侧相对的压力侧; 位于压力侧和吸力侧之间的前缘; 以及与前缘相对并跨越压力侧和吸力侧的后缘; 以及与所述翼型件的所述翼型件的第一端沿着所述吸入侧，压力侧，后缘和所述前缘连接的底座，所述底座包括靠近所述基座和所述翼型之间的连接处的非轴对称轮廓。

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