-
公开(公告)号：US20170130587A1
公开(公告)日：2017-05-11
申请号：US14936253
申请日：2015-11-09
Applicant: General Electric Company
Inventor： Soumyik Kumar Bhaumik , Brian Denver Potter , Rohit Chouhan , Georgia Fleming Brunt
CPC classification number: F01D5/145 , F01D5/141 , F01D5/147 , F01D9/041 , F02C3/04 , F05D2220/32 , F05D2220/3215 , F05D2240/301 , F05D2240/35 , F05D2250/70
Abstract: A system includes a turbine airfoil configured to be disposed in a turbine. The airfoil includes a suction side, a pressure side, and a first protrusion disposed on the suction side, a second protrusion disposed on the pressure side, or both. The suction side extends between a leading edge of the turbine airfoil and a trailing edge of the turbine airfoil in an axial direction and transverse to a longitudinal axis of the turbine airfoil, and extends a height of the turbine airfoil in a radial direction along the longitudinal axis. The pressure side is disposed opposite the suction side and extends between the leading edge of the turbine airfoil and the trailing edge of the turbine airfoil in the axial direction, and extends the height of the airfoil in the radial direction. The first protrusion is disposed on the suction side of the turbine airfoil and protrudes relative to the other portion of the suction side in a first direction transverse to both the radial and axial directions. The second protrusion is disposed on the pressure side of the turbine airfoil and protrudes relative to the other portion of the pressure side in a second direction transverse to both the radial and axial directions, and opposite the first direction.
-
12.发明申请公开(公告)号：US20170037734A1
公开(公告)日：2017-02-09
申请号：US14821234
申请日：2015-08-07
Applicant: General Electric Company
Inventor： Suryarghya Chakrabarti , Yashwanth Tummala , Letian Wang , Walter John Smith , Daniel Edward Loringer , Brian Denver Potter , Matthew John Malone
CPC classification number: F01D5/26 , F01D5/22 , F01D5/3007 , F01D25/06 , F02B33/40 , F02M35/10157 , F05D2220/40 , F05D2230/60 , F05D2260/96 , Y02T10/144
Abstract: Damping members for turbocharger assemblies, methods for providing turbocharger assemblies, and turbocharger assemblies are described herein. The damping members include bodies having shapes to fit between a recess extending into a rotor disk of a turbocharger and laterally protruding shoulders of platforms in neighboring blades of the turbocharger. The bodies dampen vibrations of the blades during rotation of the blades. The damping members may include a variety of shapes, such as a sheet, a wedge, a tapered pin, a cylindrical pin, a bent sheet, or another shape.
Abstract translation: 这里描述了用于涡轮增压器组件的阻尼构件，用于提供涡轮增压器组件的方法和涡轮增压器组件。 阻尼构件包括具有配合在延伸到涡轮增压器的转子盘的凹部和涡轮增压器的相邻叶片中的平台的横向突出的肩部之间的形状的主体。 机体在叶片转动期间会抑制叶片的振动。 阻尼构件可以包括各种形状，例如片，楔，锥形销，圆柱形销，弯曲片或其它形状。
-
公开(公告)号：US20150184519A1
公开(公告)日：2015-07-02
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.
Abstract translation: 一种具有由凹形压力侧外壁和凸形吸入侧外壁限定的翼型件的涡轮机叶片，其沿着前缘和后缘连接，并且在它们之间形成用于接收冷却剂流动的径向延伸室。 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。 肋构造可以包括具有波浪形轮廓的弧形线肋。 波浪形轮廓可以包括至少一个前后“S”形。
-
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。
-
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。
-
Patent Agency Ranking
公开(公告)号：US12071862B2
公开(公告)日：2024-08-27
申请号：US17815376
申请日：2022-07-27
Applicant: General Electric Company
CPC classification number: F01D5/26 , F01D9/041 , F05D2240/128 , F05D2260/38 , F05D2260/96
Abstract: A vibration damping system includes a vibration damping element for a turbine nozzle or blade. A body opening extends through the turbine nozzle or blade between the tip end and the base end thereof, e.g., through the airfoil among potentially other parts of the nozzle or blade. A vibration damping element includes a plurality of stacked plate members within the body opening. Each plate member is in surface contact with at least one adjacent plate member to cause friction that dampens vibration of the nozzle or blade. The body opening has an inner dimension, and each plate member has an outer dimension sized to frictionally engage the inner dimension of the body opening to damp vibration. Plate members may each include a central opening therein, and a fixed elongated body or cable may extend through the central openings. The damping element may alternatively include a helical metal ribbon spring.
-
公开(公告)号：US11976565B2
公开(公告)日：2024-05-07
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
IPC: F01D5/16
CPC classification number: F01D5/16 , 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.
-
公开(公告)号：US20240035387A1
公开(公告)日：2024-02-01
申请号：US17815376
申请日：2022-07-27
Applicant: General Electric Company
Inventor： Zachary John Snider , John McConnell Delvaux , James Tyson Balkcum, III , Brian Denver Potter
CPC classification number: F01D5/26 , F01D9/041 , F05D2240/128 , F05D2260/38 , F05D2260/96
Abstract: A vibration damping system includes a vibration damping element for a turbine nozzle or blade. A body opening extends through the turbine nozzle or blade between the tip end and the base end thereof, e.g., through the airfoil among potentially other parts of the nozzle or blade. A vibration damping element includes a plurality of stacked plate members within the body opening. Each plate member is in surface contact with at least one adjacent plate member to cause friction that dampens vibration of the nozzle or blade. The body opening has an inner dimension, and each plate member has an outer dimension sized to frictionally engage the inner dimension of the body opening to damp vibration. Plate members may each include a central opening therein, and a fixed elongated body or cable may extend through the central openings. The damping element may alternatively include a helical metal ribbon spring.
-
公开(公告)号：US11092018B2
公开(公告)日：2021-08-17
申请号：US14821234
申请日：2015-08-07
Applicant: General Electric Company
Inventor： Suryarghya Chakrabarti , Yashwanth Tummala , Letian Wang , Walter John Smith , Daniel Edward Loringer , Brian Denver Potter , Matthew John Malone
Abstract: Damping members for turbocharger assemblies, methods for providing turbocharger assemblies, and turbocharger assemblies are described herein. The damping members include bodies having shapes to fit between a recess extending into a rotor disk of a turbocharger and laterally protruding shoulders of platforms in neighboring blades of the turbocharger. The bodies dampen vibrations of the blades during rotation of the blades. The damping members may include a variety of shapes, such as a sheet, a wedge, a tapered pin, a cylindrical pin, a bent sheet, or another shape.
-
公开(公告)号：US20210172325A1
公开(公告)日：2021-06-10
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.
-
-
-
-
-
-
-
-
-
Search Results
34
records
(took 0.022 seconds)
