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公开(公告)号：US09464531B2
公开(公告)日：2016-10-11
申请号：US14055095
申请日：2013-10-16
Applicant: General Electric Company
Inventor： Christian Michael Hansen , Michael James Healy , Brian Denver Potter
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。
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公开(公告)号：US09404376B2
公开(公告)日：2016-08-02
申请号：US14064461
申请日：2013-10-28
Applicant: General Electric Company
Inventor： Brian Denver Potter , Gary Charles Liotta
IPC: F01D11/00
CPC classification number: F01D11/006 , F01D11/001
Abstract: A sealing component for reducing secondary airflow in a turbine system includes a first end segment configured to be disposed between, and retained in a radial direction by, a first land on a first rotor disk and a first turbine bucket platform operatively coupled to the first rotor disk. Also included is a second end segment configured to be disposed between, and retained in a radial direction by, a second land on a second rotor disk and a second turbine bucket platform operatively coupled to the second rotor disk. Further included is a main body portion extending axially from the first end segment to the second end segment.
Abstract translation: 用于减少涡轮机系统中的二次气流的密封部件包括：第一端部段，其构造成设置在第一转子盘上的第一平台之间并且沿着径向方向保持在第一转子盘上的第一平台和可操作地联接到第一转子的第一涡轮机叶片平台 磁盘。 还包括被配置为设置在第二转子盘上的第二平台和可操作地连接到第二转子盘的第二涡轮叶片平台之间并保持在径向方向上的第二端部段。 还包括从第一端段向第二端段轴向延伸的主体部分。
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公开(公告)号：US11187089B2
公开(公告)日：2021-11-30
申请号：US16708999
申请日：2019-12-10
Applicant: General Electric Company
Abstract: Damper stacks, rotor blades, and turbomachines are provided. A rotor blade includes a main body including a shank and an airfoil extending radially outwardly from the shank. The rotor blade further includes a damping passage defined in the main body, the damping passage extending radially through the main body. The rotor blade further includes a damper stack disposed within the damping passage, the damper stack including a plurality of damper pins, each of the plurality of damper pins in contact with a neighboring damper pin.
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公开(公告)号：US10443408B2
公开(公告)日：2019-10-15
申请号：US14844545
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 aligned with and axially spaced from a second end portion and a retention pin that is coaxially aligned with and disposed between the first end portion and the second end portion. The retention pin couples the first end portion to the second end portion. The damper pin further includes a plurality of rings coaxially aligned with and disposed along the retention pin between the first end portion and the second end portion. The first end portion, the second end portion and the plurality of rings define a generally arcuate outer surface of the damper pin that is configured to contact with a groove defined between the adjacent turbine blades.
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公开(公告)号：US20150114001A1
公开(公告)日：2015-04-30
申请号：US14064461
申请日：2013-10-28
Applicant: General Electric Company
Inventor： Brian Denver Potter , Gary Charles Liotta
IPC: F01D11/00
CPC classification number: F01D11/006 , F01D11/001
Abstract: A sealing component for reducing secondary airflow in a turbine system includes a first end segment configured to be disposed between, and retained in a radial direction by, a first land on a first rotor disk and a first turbine bucket platform operatively coupled to the first rotor disk. Also included is a second end segment configured to be disposed between, and retained in a radial direction by, a second land on a second rotor disk and a second turbine bucket platform operatively coupled to the second rotor disk. Further included is a main body portion extending axially from the first end segment to the second end segment.
Abstract translation: 用于减少涡轮机系统中的二次气流的密封部件包括：第一端部段，其构造成设置在第一转子盘上的第一平台之间并且沿着径向方向保持在第一转子盘上的第一平台和可操作地联接到第一转子的第一涡轮机叶片平台 磁盘。 还包括被配置为设置在第二转子盘上的第二平台和可操作地连接到第二转子盘的第二涡轮叶片平台之间并保持在径向方向上的第二端部段。 还包括从第一端段轴向延伸到第二端段的主体部分。
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Patent Agency Ranking
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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公开(公告)号：US20150101349A1
公开(公告)日：2015-04-16
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: F01D5/30
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
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公开(公告)号：US20240035384A1
公开(公告)日：2024-02-01
申请号：US17815372
申请日：2022-07-27
Applicant: General Electric Company
Inventor： Zachary John Snider , Brad Wilson VanTassel , Brian Denver Potter , John McConnell Delvaux
CPC classification number: F01D25/04 , F01D25/06 , F05D2220/32 , F05D2260/96
Abstract: A vibration dampening system includes a vibration dampening element for a turbine nozzle or blade. A body opening extends through the turbine nozzle or blade, e.g., through the airfoil among potentially other parts of the nozzle or blade. A vibration dampening element includes a plurality of stacked damper pins within the body opening. The damper pins include an outer body having an inner opening, a first end surface and an opposing second end surface; and an inner body nested and movable within the inner opening of the outer body. The end surfaces frictionally engage to dampen vibration. The inner body has a first central opening including a first portion configured to engage an elongated body therein and an outer surface configured to frictionally engage a portion of the inner opening of the outer body to dampen vibration.
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公开(公告)号：US11248475B2
公开(公告)日：2022-02-15
申请号：US16709050
申请日：2019-12-10
Applicant: General Electric Company
Abstract: Damper stacks, rotor blades, and turbomachines are provided. A rotor blade includes a main body including a shank and an airfoil extending radially outwardly from the shank. The rotor blade further includes a platform surrounding the main body, the platform comprising a slash face. The rotor blade further includes a damper stack disposed at the slash face and extending generally along an axial direction. The damper stack includes a plurality of damper pins, each of the plurality of damper pins being in contact with a neighboring damper pin.
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公开(公告)号：US09995149B2
公开(公告)日：2018-06-12
申请号：US14143443
申请日：2013-12-30
Applicant: General Electric Company
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 having an airfoil defined by a concave shaped pressure side outer wall and a convex shaped suction side outer wall that connect along leading and trailing edges and, therebetween, form a radially extending chamber for receiving the flow of a coolant. The turbine blade may further include a rib configuration that partitions the chamber into radially extending flow passages. The rib configuration may include a camber line rib having a wavy profile. The wavy profile may include at least one back-and-forth “S” shape.
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