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    FLOWPATH BOUNDARY AND ROTOR ASSEMBLIES IN GAS TURBINES
    14.
    发明申请
    FLOWPATH BOUNDARY AND ROTOR ASSEMBLIES IN GAS TURBINES 审中-公开

    公开(公告)号：US20160186592A1

    公开(公告)日：2016-06-30

    申请号：US14587736

    申请日：2014-12-31

    Applicant: General Electric Company

    Inventor： Michael James Healy ,  Jeremy Peter Latimer

    IPC: F01D11/00 ,  F01D5/30 ,  F01D5/06

    CPC classification number: F01D5/3007 ,  F01D11/08 ,  F05D2240/11 ,  Y02T50/671 ,  Y02T50/673

    Abstract: A gas turbine that having a flowpath having a rotor assembly that includes: a first rotor wheel supporting a first rotor blade having a platform that defines a first axial section of an inner boundary of the flowpath; a second rotor wheel supporting a second rotor blade having a platform that defines a second axial section of the inner boundary of the flowpath; and an annulus filler that includes an outboard surface that defines at least part of a third axial section of the inner boundary of the flowpath occurring between the first axial section and the second axial section of the inner boundary of the flowpath. The first rotor wheel may include an axial connector for axially engaging a mating surface formed on a radially innermost face of the first rotor blade and a mating surface formed on a radially innermost face of the annulus filler.

    LOCKING SPACER ASSEMBLY
    15.
    发明申请
    LOCKING SPACER ASSEMBLY 审中-公开
    锁定间隔装置

    公开(公告)号：US20150101350A1

    公开(公告)日：2015-04-16

    申请号：US14055114

    申请日：2013-10-16

    Applicant: General Electric Company

    Inventor： Michael James Healy ,  Brian Denver Potter

    IPC: F01D5/30

    CPC classification number: F01D5/303 ,  F01D5/3038 ,  F01D5/32

    Abstract: A locking spacer assembly for securing adjacent rotor blades includes a first end piece configured to fit into a space between the platforms of adjacent rotor blades. The first end piece comprises an outer surface and an inner surface. The outer surface has a profile that is adapted to project into the attachment slot. A second end piece is configured to fit into a space between the platforms. The second end piece comprises an outer surface and an inner surface. The outer surface has a profile that is adapted to project into the attachment slot. The inner surfaces of the first and second end pieces generally face each other. The first end piece and the second end piece are bonded together either directly or via a spacer block that is inserted between the inner surfaces.

    Abstract translation: 用于固定相邻转子叶片的锁定间隔件组件包括构造成装配到相邻转子叶片的平台之间的空间中的第一端件。 第一端件包括外表面和内表面。 外表面具有适于突出到附接槽中的轮廓。 第二端件构造成适合平台之间的空间。 第二端件包括外表面和内表面。 外表面具有适于突出到附接槽中的轮廓。 第一和第二端片的内表面通常面对彼此。 第一端片和第二端片直接地或通过插入在内表面之间的间隔块结合在一起。

    LOCKING SPACER ASSEMBLY
    16.
    发明申请
    LOCKING SPACER ASSEMBLY 有权
    锁定间隔装置

    公开(公告)号：US20150101348A1

    公开(公告)日：2015-04-16

    申请号：US14055095

    申请日：2013-10-16

    Applicant: General Electric Company

    Inventor： Christian Michael Hansen ,  Michael James Healy ,  Brian Denver Potter

    IPC: F01D5/30

    CPC classification number: F01D5/303 ,  F01D5/3038 ,  F01D5/32

    Abstract: Locking spacer assemblies, rotor assemblies and turbomachines are provided. In one embodiment, a locking spacer assembly includes a first end piece and a second end piece each configured to fit into a space between platforms of adjacent rotor blades, the first end piece and second end piece each comprising an outer surface and an inner surface, the outer surface having a profile adapted to project into an attachment slot, wherein the inner surfaces of the first and second end pieces generally face each other. The locking spacer assembly further includes an actuator movable between the inner surfaces, the actuator comprising a projection configured to engage the inner surface, the actuator further comprising a plurality of locating protrusions extending from the projection, the locating protrusions configured to fit within locating channels defined in the first end piece and the second end piece.

    Abstract translation: 提供了锁定间隔件组件，转子组件和涡轮机。 在一个实施例中，锁定间隔件组件包括第一端部件和第二端部件，每个第一端部件和第二端部件被构造成装配到相邻转子叶片的平台之间的空间中，第一端部件和第二端件每个包括外表面和内表面， 所述外表面具有适于突出到附接槽中的轮廓，其中所述第一和第二端片的内表面通常面对彼此。 所述锁定间隔件组件还包括可在所述内表面之间移动的致动器，所述致动器包括构造成接合所述内表面的突出部，所述致动器还包括从所述突起延伸的多个定位突起，所述定位突起被配置成适合定位的定位通道 在第一端件和第二端件中。

    Compressor stator vane airfoils
    17.
    发明授权
    Compressor stator vane airfoils 有权

    公开(公告)号：US11643933B1

    公开(公告)日：2023-05-09

    申请号：US17956992

    申请日：2022-09-30

    Applicant: General Electric Company

    Inventor： Matthew John McKeever ,  Kevin Michael Barnett ,  Michael James Healy

    IPC: F01D5/14 ,  F01D9/02

    CPC classification number: F01D5/141 ,  F01D9/02 ,  F05D2250/74

    Abstract: A stator vane includes an airfoil having an airfoil shape. The airfoil shape has a nominal profile substantially in accordance with Cartesian coordinate values of X, Y, and Z set forth in one of TABLE I or TABLE II. The Cartesian coordinate values of X, Y, and Z are defined relative to a point data origin at a base of the airfoil. The Cartesian coordinate values of X, Y, and Z are non-dimensional values that are convertible to dimensional distances expressed in a unit of distance by multiplying the Cartesian coordinate values of X, Y, and Z by a scaling factor of the airfoil in the unit of distance. The X and Y values are connected by smooth continuing arcs to define airfoil profile sections at each Z value. The airfoil profile sections at Z values are joined smoothly with one another to form a complete airfoil shape.

    SPLIT-LINE STATOR VANE ASSEMBLY
    18.
    发明申请
    SPLIT-LINE STATOR VANE ASSEMBLY 有权

    公开(公告)号：US20220381150A1

    公开(公告)日：2022-12-01

    申请号：US17389562

    申请日：2021-07-30

    Applicant: General Electric Company

    Inventor： Michael James Healy ,  Sabarinath Devarajan ,  Carlos Alberto Cardoza

    IPC: F01D9/02

    Abstract: A compressor section includes a compressor casing that has an upper casing portion coupled to a lower casing portion such that a split-line is defined between the upper casing portion and the lower casing portion. A split-line stator vane assembly includes a first split-line stator vane that has a first shank with a first platform portion and a first mounting portion extends radially outward of the first platform portion. A first airfoil extends radially inward of the platform portion. The first platform portion includes a protrusion that extends circumferentially beyond the split-line. A second split-line stator vane having second shank with a second platform portion and a second mounting portion extends radially outward of the second platform portion. A second airfoil extends radially inward of the second platform portion. The second platform portion includes a recess that extends circumferentially away from the split-line.

    LOCKING SPACER ASSEMBLY
    20.
    发明申请
    LOCKING SPACER ASSEMBLY 有权
    锁定间隔装置

    公开(公告)号：US20150101351A1

    公开(公告)日：2015-04-16

    申请号：US14055124

    申请日：2013-10-16

    Applicant: General Electric Company

    Inventor： Michael James Healy ,  Brian Denver Potter

    IPC: F01D5/30

    CPC classification number: F01D5/303 ,  F01D5/3038 ,  F01D5/32

    Abstract: Locking spacer assemblies and turbomachines are provided. In one embodiment, a locking spacer assembly includes a spacer, the spacer including a platform and a plurality of legs extending generally radially inward from the platform. The locking spacer assembly further includes a clamp configured to contact and cause elastic deformation of each of the plurality of legs in a generally axial direction towards each other. The locking spacer assembly further includes a locking lug configured to contact and impart a force against each of the plurality of legs in an opposite generally axial direction.

    Abstract translation: 提供了锁定间隔件组件和涡轮机。 在一个实施例中，锁定间隔件组件包括间隔件，间隔件包括平台和从平台大致径向向内延伸的多个腿。 锁定间隔件组件还包括夹具，该夹具构造成使多个腿中的每一个在大致轴向方向上彼此接触并引起弹性变形。 锁定间隔件组件还包括锁定凸耳，所述锁定凸耳构造成在相反的大致轴向方向上接触并向所述多个支腿中的每一个施加力。

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