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    Turbine blade with tip shroud cooling passage
    2.
    发明授权
    Turbine blade with tip shroud cooling passage 有权

    公开(公告)号：US11225872B2

    公开(公告)日：2022-01-18

    申请号：US16674059

    申请日：2019-11-05

    Applicant: General Electric Company

    Inventor： Melbourne James Myers ,  Michael Anthony Wondrasek ,  Mary Virginia Holloway ,  Luke C. Sponseller ,  Brandon Joseph Kerins

    IPC: F01D5/18

    Abstract: A turbine blade includes a root for fixing the turbine blade to a turbine rotor; and an airfoil coupled to the root, the airfoil including a suction side and a pressure side, and at least one internal wall defining a coolant chamber in the airfoil for delivering a coolant through the airfoil. A tip shroud is coupled to a radially outer end of the airfoil by a suction side fillet and a pressure side fillet. The tip shroud includes a shroud body defining a substantially trident-shaped shroud cooling passage including: a trunk cooling passage, a center cooling passage in fluid communication with the trunk cooling passage, a suction side cooling passage in fluid communication with the trunk cooling passage, and a pressure side cooling passage in fluid communication with the trunk cooling passage. The center cooling passage is fluidly coupled to the coolant chamber to receive a coolant.

    Turbine bucket with a cooling circuit having an asymmetric root turn
    3.
    发明授权
    Turbine bucket with a cooling circuit having an asymmetric root turn 有权

    公开(公告)号：US11187085B2

    公开(公告)日：2021-11-30

    申请号：US16713376

    申请日：2019-12-13

    Applicant: General Electric Company

    Inventor： William Scott Zemitis ,  Luke C. Sponseller ,  Michael Gordon Sherman

    IPC: F01D5/18

    Abstract: A turbine bucket may include a platform, an airfoil extending from the platform at an intersection thereof, and a cooling circuit extending within the platform and the airfoil. The cooling circuit may include a root turn with an asymmetric shape to reduce stress concentrations therein. The asymmetric shape of the root turn may be asymmetrical along a path between a pressure side of the airfoil and a suction side of the airfoil. The asymmetric shape of the root turn may be asymmetrical within a plane defined by a radial direction and a circumferential direction.

    TURBINE BLADE WITH TIP SHROUD COOLING PASSAGE
    4.
    发明申请
    TURBINE BLADE WITH TIP SHROUD COOLING PASSAGE 有权

    公开(公告)号：US20210131291A1

    公开(公告)日：2021-05-06

    申请号：US16674059

    申请日：2019-11-05

    Applicant: General Electric Company

    Inventor： Melbourne James Myers ,  Michael Anthony Wondrasek ,  Mary Virginia Holloway ,  Luke C. Sponseller ,  Brandon Joseph Kerins

    IPC: F01D5/18

    Abstract: A turbine blade includes a root for fixing the turbine blade to a turbine rotor; and an airfoil coupled to the root, the airfoil including a suction side and a pressure side, and at least one internal wall defining a coolant chamber in the airfoil for delivering a coolant through the airfoil. A tip shroud is coupled to a radially outer end of the airfoil by a suction side fillet and a pressure side fillet. The tip shroud includes a shroud body defining a substantially trident-shaped shroud cooling passage including: a trunk cooling passage, a center cooling passage in fluid communication with the trunk cooling passage, a suction side cooling passage in fluid communication with the trunk cooling passage, and a pressure side cooling passage in fluid communication with the trunk cooling passage. The center cooling passage is fluidly coupled to the coolant chamber to receive a coolant.

    AIRFOIL SHAPE FOR TURBINE ROTOR BLADES
    5.
    发明申请
    AIRFOIL SHAPE FOR TURBINE ROTOR BLADES 审中-公开

    公开(公告)号：US20200131912A1

    公开(公告)日：2020-04-30

    申请号：US16176275

    申请日：2018-10-31

    Applicant: General Electric Company

    Inventor： Melbourne James Myers ,  Sylvain Pierre ,  Michael Gordon Sherman ,  Luke C. Sponseller ,  Zhirui Dong ,  Le Trong Tran

    IPC: F01D5/14 ,  F02C3/04

    Abstract: A turbine rotor blade having an airfoil that includes a pressure side portion of a nominal airfoil profile substantially in accordance with Cartesian coordinate values of X, Y, and Z of a pressure side as set forth in Table I. The Cartesian coordinate values of X, Y, and Z are non-dimensional values from 0% to 100% convertible to dimensional distances by multiplying the Cartesian coordinate values of X, Y and Z by a height of the airfoil defined along the Z axis. The X and Y values of the pressure side are coordinate values that, when connected by smooth continuing arcs, define pressure side sections of the pressure side portion of the nominal airfoil profile at each Z coordinate value. The pressure side sections may be joined smoothly with one another to form the pressure side portion.

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