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    Locking spacer assembly
    23.
    发明授权
    Locking spacer assembly 有权
    锁定垫片组件

    公开(公告)号：US09518471B2

    公开(公告)日：2016-12-13

    申请号：US14055106

    申请日：2013-10-16

    Applicant: General Electric Company

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

    IPC: F01D5/32 ,  F01D5/30

    CPC classification number: F01D5/303 ,  F01D5/3038 ,  F01D5/3053 ,  F01D5/32 ,  F05D2240/80 ,  F05D2260/30

    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, the projection comprising a first surface and a second surface formed on the projection and configured to engage the inner surfaces, the first and second surfaces generally perpendicular to radial.

    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，所述致动器包括突起，所述突起包括第一表面和形成在所述突起上的第二表面，并且被配置为接合所述内表面，所述第一表面和所述第二表面大致垂直于 径向

    Locking spacer assembly inserted between rotor blades
    24.
    发明授权
    Locking spacer assembly inserted between rotor blades 有权
    插入在转子叶片之间的锁定间隔件组件

    公开(公告)号：US09512732B2

    公开(公告)日：2016-12-06

    申请号：US14055091

    申请日：2013-10-16

    Applicant: General Electric Company

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

    IPC: F01D5/32 ,  F01D5/30

    CPC classification number: F01D5/323 ,  F01D5/3038 ,  F01D5/3053 ,  F01D5/32 ,  F05D2240/80 ,  F05D2260/30

    Abstract: A locking spacer assembly for securing adjacent rotor blades includes a first end piece having a platform portion and a root portion that define an angled first inner surface of the first end piece. The root portion defines a first projection adapted to project into a recess portion of the attachment slot. A second end piece fits between the first inner surface and a sidewall portion of the attachment slot and includes a platform portion and a root portion that define a second projection adapted to project into a recess portion of the attachment slot. The platform portion and the root portion define an angled second inner surface and that is configured to mate with the first inner surface. A borehole extends through the platform portion of the first end piece and the root portion of the second end piece and a fastener extends through the borehole.

    Abstract translation: 用于固定相邻转子叶片的锁定间隔件组件包括具有平台部分和限定第一端件的成角度的第一内表面的根部的第一端部件。 根部限定适于突出到附接槽的凹部中的第一突起。 第二端部件装配在附接槽的第一内表面和侧壁部分之间，并且包括平台部分和根部，其限定适于突出到附接槽的凹部中的第二突出部。 平台部分和根部部分限定成角度的第二内表面，并且被配置为与第一内表面配合。 钻孔延伸穿过第一端件的平台部分和第二端件的根部，并且紧固件延伸穿过钻孔。

    INTERIOR COOLING CIRCUITS IN TURBINE BLADES
    25.
    发明申请
    INTERIOR COOLING CIRCUITS IN TURBINE BLADES 有权
    涡轮叶片内部冷却电路

    公开(公告)号：US20150184520A1

    公开(公告)日：2015-07-02

    申请号：US14143472

    申请日：2013-12-30

    Applicant: General Electric Company

    Inventor： Brian Denver Potter ,  Gregory Thomas Foster

    IPC: F01D5/18

    CPC classification number: F01D5/187 ,  F01D5/188 ,  F05D2240/305 ,  F05D2240/306 ,  F05D2250/71 ,  F05D2250/711 ,  F05D2250/712 ,  F05D2250/713 ,  F05D2250/75 ,  F05D2260/22141 ,  Y02T50/676

    Abstract: A turbine blade that includes an airfoil and a radially extending chamber therein for a coolant. The turbine blade may also include a rib configuration that partitions the chamber into radially extending flow passages. The rib configuration may include: a camber line rib that defines a near-wall flow chamber; and traverse ribs extending between the camber line rib and one of the outer walls so to divide the near-wall flow chamber into successively stacked flow passages that each include a segment of the camber line rib. The segment of the camber line rib of one of the flow passages may have a narrowing profile that includes a profile that narrows from opposing ends toward a neck disposed therebetween.

    Abstract translation: 一种涡轮机叶片，其包括用于冷却剂的翼型件和径向延伸的室。 涡轮叶片还可以包括将腔室分隔成径向延伸的流动通道的肋构型。 所述肋构造可以包括：限定近壁流动室的弧形线肋; 以及在所述弯曲肋条和所述外壁中的一个之间延伸的横向肋，以便将所述近壁流动室分成依次层叠的流动通道，每个所述流动通道包括所述弯曲肋条的一段。 一个流动通道的弧形线肋的段可以具有变窄轮廓，其包括从相对端变窄到设置在它们之间的颈部的轮廓。

    LOCKING SPACER ASSEMBLY
    26.
    发明申请
    LOCKING SPACER ASSEMBLY 有权
    锁定间隔装置

    公开(公告)号：US20150101347A1

    公开(公告)日：2015-04-16

    申请号：US14055091

    申请日：2013-10-16

    Applicant: General Electric Company

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

    IPC: F01D5/32

    CPC classification number: F01D5/323 ,  F01D5/3038 ,  F01D5/3053 ,  F01D5/32 ,  F05D2240/80 ,  F05D2260/30

    Abstract: A locking spacer assembly for securing adjacent rotor blades includes a first end piece having a platform portion and a root portion that define an angled first inner surface of the first end piece. The root portion defines a first projection adapted to project into a recess portion of the attachment slot. A second end piece fits between the first inner surface and a sidewall portion of the attachment slot and includes a platform portion and a root portion that define a second projection adapted to project into a recess portion of the attachment slot. The platform portion and the root portion define an angled second inner surface and that is configured to mate with the first inner surface. A borehole extends through the platform portion of the first end piece and the root portion of the second end piece and a fastener extends through the borehole.

    Abstract translation: 用于固定相邻转子叶片的锁定间隔件组件包括具有平台部分和限定第一端件的成角度的第一内表面的根部的第一端部件。 根部限定适于突出到附接槽的凹部中的第一突起。 第二端部件装配在附接槽的第一内表面和侧壁部分之间，并且包括平台部分和根部，其限定适于突出到附接槽的凹部中的第二突出部。 平台部分和根部部分限定成角度的第二内表面，并且被配置为与第一内表面配合。 钻孔延伸穿过第一端件的平台部分和第二端件的根部，并且紧固件延伸穿过钻孔。

    Damper pin for a turbine blade
    28.
    发明授权
    Damper pin for a turbine blade 有权

    公开(公告)号：US10385701B2

    公开(公告)日：2019-08-20

    申请号：US14844317

    申请日：2015-09-03

    Applicant: General Electric Company

    Inventor： Spencer A. Kareff ,  Brian Denver Potter ,  Ariel Caesar Prepena Jacala

    IPC: F01D5/22

    Abstract: A damper pin for damping adjacent turbine blades coupled to a rotor shaft includes a first end portion that is axially spaced from a second end portion and a spring member that extends axially from an inner surface of the first end portion to an inner surface of the second end portion. The first end portion, the spring member and the second end portion define a generally arcuate top portion of the damper pin. The top portion is configured to contact with a groove defined between the adjacent turbine blades.

    Turbine bucket assembly and turbine system
    29.
    发明授权
    Turbine bucket assembly and turbine system 有权

    公开(公告)号：US10267156B2

    公开(公告)日：2019-04-23

    申请号：US14290076

    申请日：2014-05-29

    Applicant: GENERAL ELECTRIC COMPANY

    Inventor： Dwight Eric Davidson ,  Michael David McDufford ,  Brian Denver Potter ,  Stephen Joseph Balsone ,  Stephen Paul Wassynger

    IPC: F01D5/14 ,  F01D5/16 ,  F01D5/22 ,  F01D5/28 ,  F01D5/30

    Abstract: A turbine bucket assembly and turbine system are disclosed. The turbine bucket assembly includes a single-lobe joint having an integral platform, the joint having a first axial length; a segmented airfoil having a root segment extending radially outward from the platform and a tip segment coupled to the root segment, the tip segment having a second axial length, which is less than the first axial length; and a turbine wheel defining a receptacle with a geometry corresponding to the single-lobe joint and being coupled to the single-lobe joint. The tip segment includes a tip segment material, the root segment includes a root segment material, and the turbine wheel includes a turbine wheel material, the root segment material and the turbine wheel material having a lower heat resistance and a higher thermal expansion than the tip segment material.

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