公开(公告)号：US20170067350A1

公开(公告)日：2017-03-09

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

CPC classification number: F01D5/22 ,  F05D2220/32 ,  F05D2250/141 ,  Y02T50/672

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.

Abstract translation: 用于阻尼连接到转子轴的相邻涡轮机叶片的阻尼器销包括与第二端部轴向对准并与其轴向间隔开的第一端部和与第一端部与第二端部同轴对准并且设置在第二端部之间的固定销 端部。 保持销将第一端部连接到第二端部。 阻尼销进一步包括沿第一端部和第二端部之间的保持销共同对准并设置的多个环。 所述第一端部，所述第二端部和所述多个环限定所述阻尼器销的大致弧形的外表面，所述外表面构造成与限定在所述相邻涡轮叶片之间的凹槽接触。

公开(公告)号：US20170067348A1

公开(公告)日：2017-03-09

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

CPC classification number: F01D5/22 ,  F05D2220/32 ,  F05D2250/25 ,  Y02T50/671 ,  Y02T50/673

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.

Abstract translation: 用于阻尼与转子轴连接的相邻涡轮机叶片的阻尼器销包括与第二端部轴向隔开的第一端部和从第一端部的内表面轴向延伸到第二端部的内表面的弹簧构件 端部。 第一端部，弹簧构件和第二端部限定阻尼销的大致弓形顶部。 顶部构造成与限定在相邻涡轮叶片之间的凹槽接触。

公开(公告)号：US09341071B2

公开(公告)日：2016-05-17

申请号：US14055124

申请日：2013-10-16

Applicant: General Electric Company

Inventor： Michael James Healy ,  Brian Denver Potter

IPC: F01D5/30 ,  F01D5/32

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。

公开(公告)号：US20160040537A1

公开(公告)日：2016-02-11

申请号：US14453914

申请日：2014-08-07

Applicant: General Electric Company

Inventor： David Randolph Spracher ,  Kevin Leon Bruce ,  John Wesley Harris, JR. ,  Brian Denver Potter ,  William Scott Zemitis

IPC: F01D5/22

CPC classification number: F01D5/225 ,  F01D5/147 ,  Y02T50/673

Abstract: A mid-span shroud assembly for a turbine blade includes a pressure side shroud body defining a spar pocket and a fastener hole and a suction side shroud body defining a spar pocket and a fastener hole. The mid-span shroud assembly further includes a spar having a first end portion which extends within the spar pocket of the pressure side shroud body and a second end portion which extends within the spar pocket of the suction side shroud body. The spar is formed to extend through a bore hole of the turbine blade. A fastener is formed to extend through the fastener hole of the pressure side shroud body, a fastener orifice of the turbine blade and the fastener hole of the suction side shroud body to provide a clamping force to hold the pressure side and suction side shroud bodies against the airfoil.

Abstract translation: 用于涡轮叶片的中跨护罩组件包括限定翼梁窝和紧固件孔的压力侧护罩主体和限定翼梁窝和紧固件孔的吸力侧护罩主体。 中跨护罩组件还包括翼梁，翼梁具有在压力侧护罩主体的翼梁槽内延伸的第一端部和在吸力侧护罩主体的翼梁槽内延伸的第二端部。 翼梁形成为延伸穿过涡轮机叶片的钻孔。 紧固件形成为延伸穿过压力侧护罩主体的紧固件孔，涡轮叶片的紧固件孔口和吸力侧护罩主体的紧固件孔，以提供夹紧力以将压力侧和吸力侧护罩体抵靠 机翼。