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21.发明授权公开(公告)号：US10047613B2
公开(公告)日：2018-08-14
申请号：US14841056
申请日：2015-08-31
Applicant: General Electric Company
Inventor： Cody Jermaine Ford , Brad Wilson VanTassel
Abstract: A gas turbine component is provided. The gas turbine component includes an airfoil having a leading edge, a trailing edge, a suction side extending from the leading edge to the trailing edge, and a pressure side extending from the leading edge to the trailing edge opposite the suction side. The gas turbine component also includes a thermal barrier coating applied to the airfoil pressure side such that an uncoated margin is defined on the pressure side at the trailing edge.
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公开(公告)号：US20180126499A1
公开(公告)日：2018-05-10
申请号：US15346042
申请日：2016-11-08
Applicant: General Electric Company
Inventor： Cem Murat Eminoglu , Yan Cui , Cody Jermaine Ford , Brad Wilson VanTassel
CPC classification number: B23P6/005 , B23K1/0018 , B23K2101/001 , B23P6/002 , F01D5/005 , F01D5/28 , F01D9/02 , F05D2220/32 , F05D2230/80 , F05D2300/175
Abstract: A coupon for repairing a part is disclosed. The coupon includes an outwardly threaded body configured to mate with an inwardly threaded opening in a damaged area of the part. The part and/or coupon may include a superalloy. The threaded arrangement converts tensile stresses into shear stresses that allow the repair to exhibit material characteristics as good as or better than the superalloy. A method of using the coupon to repair a part using brazing, and a turbomachine part using the coupon, are also disclosed.
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公开(公告)号：US20160362988A1
公开(公告)日：2016-12-15
申请号：US15245985
申请日：2016-08-24
Applicant: General Electric Company
Inventor： John David Ward , Kelvin Rono Aaron , James Ryan Connor , Melbourne James Myers , Brad Wilson VanTassel
IPC: F01D5/22
CPC classification number: F01D5/225 , F01D5/005 , F05D2220/32 , F05D2230/10 , F05D2230/50 , F05D2230/80 , F05D2260/94 , F05D2270/332 , Y10T29/49234 , Y10T83/04
Abstract: A method is provided for modifying an airfoil shroud located at a tip of a blade of an airfoil, the airfoil shroud having a first end edge, a second end edge, a leading edge, and a trailing edge. The method includes locating a reference location in the first end edge of the airfoil shroud, the reference location including a portion of a seal rail extending circumferentially from a radially outer surface of the airfoil shroud, and a fillet extending from the radially outer surface and positioned directly adjacent to the seal rail. The method further includes forming a relief cut in the seal rail and fillet without performing a weld process on the airfoil shroud to remove the reference location, and installing the airfoil shroud in a turbomachine directly following forming the relief cut, wherein modifying the airfoil shroud is complete following forming the relief cut.
Abstract translation: 提供了一种用于改变位于翼型件的叶片的尖端处的翼型护罩的方法，翼型护罩具有第一端边缘，第二端边缘，前缘和后缘。 该方法包括将参考位置定位在翼型护罩的第一端边缘中，参考位置包括从翼型护罩的径向外表面周向延伸的密封轨道的一部分，以及从径向外表面延伸的圆角， 直接靠近密封轨。 该方法还包括在密封导轨和圆角上形成浮雕切口，而不对翼型护罩进行焊接处理以去除参考位置，并且在形成浮雕切割之后将翼型件护罩直接安装在涡轮机中，其中修改翼型护罩是 完成以后形成救济切割。
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24.发明申请SYSTEM AND METHOD FOR CONTROLLING OPERATION OF A GAS TURBINE BASED POWER PLANT 审中-公开一种控制燃气轮机动力装置运行的系统和方法公开(公告)号：US20150081121A1
公开(公告)日：2015-03-19
申请号：US14488723
申请日：2014-09-17
Applicant: General Electric Company
Inventor： Rex Allen Morgan , James Tyson Balkcum, III , Stephen R. Watts , Harold Lamar Jordan, JR. , Brad Wilson VanTassel
Abstract: A system for controlling a gas turbine power plant includes a plurality of sensors configured to transmit signals indicative of one or more operating parameters of the gas turbine, and a control system in electronic communication with each sensor. The control system is configured to compute cumulative wear for one or more hardware components of the gas turbine based at least in part on the signals. Instructions are inputted into the control system which indicates a desired operational mode for the gas turbine. The control system may then compute a hardware consumption rate based at least in part on the cumulative wear. The hardware consumption rate may then be displayed to an operator via a display device. The operator may use the hardware consumption rate to determine potential economic impact of operating the gas turbine at the desired operational mode.
Abstract translation: 用于控制燃气轮机发电厂的系统包括多个传感器，其被配置为传送指示燃气轮机的一个或多个操作参数的信号，以及与每个传感器电子通信的控制系统。 控制系统被配置为至少部分地基于信号来计算燃气涡轮机的一个或多个硬件部件的累积磨损。 指令被输入到指示燃气轮机的期望操作模式的控制系统中。 然后，控制系统可以至少部分地基于累积磨损来计算硬件消耗率。 然后可以经由显示装置向操作者显示硬件消耗率。 操作员可以使用硬件消耗率来确定在期望的操作模式下操作燃气轮机的潜在的经济影响。
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公开(公告)号：US12091982B2
公开(公告)日：2024-09-17
申请号：US17806317
申请日：2022-06-10
Applicant: General Electric Company
Inventor： Brandon Lee Cox , Brad Wilson VanTassel , Benjamin Paul Lacy
CPC classification number: F01D25/08 , F01D5/12 , F01D9/065 , F01D25/10 , F05D2220/30 , F05D2240/81 , F05D2260/941
Abstract: A turbine component includes a first structure exposed to a hot gas path and a second structure integral with the first structure but isolated from the hot gas path. A first fluid passage in the first structure delivers a thermal transfer fluid, e.g., air, through the first structure to cool the first structure. A second fluid passage is defined within the second structure and is in fluid communication with the first fluid passage. After heat transfer in the first structure, the thermal transfer fluid is hotter than a temperature of the second structure and thus increases the temperature of the second structure. The heat transfer to the second structure reduces a temperature difference between the first structure and the second structure that would, without heating, cause thermal stress between the structures. The heating of the second structure reduces the need for early maintenance and lengthens the lifespan of the component.
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Patent Agency Ranking
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：US11572803B1
公开(公告)日：2023-02-07
申请号：US17816574
申请日：2022-08-01
Applicant: General Electric Company
Inventor： Benjamin Paul Lacy , Ibrahim Sezer , Brad Wilson VanTassel
Abstract: A turbine airfoil includes a body including a wall defining pressure and suction sides, and a leading edge extending between the pressure and suction sides. A cooling circuit inside the wall of the body includes at least one of: a) a suction side to pressure side cooling sub-circuit including a first cooling passage(s) extending from the suction side to the pressure side around the leading edge to a first plenum, and a plurality of first film cooling holes communicating with the first plenum and extending through the wall on the pressure side; and b) a pressure side to suction side cooling sub-circuit including second cooling passage(s) extending from the pressure side to the suction side around the leading edge to a second plenum, and a plurality of second film cooling holes communicating with the second plenum and extending through the wall on the suction side.
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公开(公告)号：US11085374B2
公开(公告)日：2021-08-10
申请号：US16701408
申请日：2019-12-03
Applicant: General Electric Company
Inventor： Travis J Packer , Brad Wilson VanTassel
Abstract: An impingement insert for HGP component may include a hollow body having a longitudinal extent, an exterior surface and an interior surface. The hollow body may include a first side wall, a second side wall contiguous with the first side wall at a first end of each, the second side wall is flexibly movable relative to the first side wall. A spring element is contiguous with a second end of each of the first side wall and the second side wall, and extends along at least a portion of the longitudinal extent of the hollow body and into the hollow body between the first side wall and the second side wall. The spring element biases the side walls to an expanded position from a compressed position of the hollow body. Cooling passages pass between the exterior surface and the interior surface of the hollow body in both side walls.
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公开(公告)号：US10989068B2
公开(公告)日：2021-04-27
申请号：US16040062
申请日：2018-07-19
Applicant: General Electric Company
Inventor： Travis J Packer , Benjamin Paul Lacy , Ibrahim Sezer , Zachary John Snider , Brad Wilson VanTassel
Abstract: Turbine shrouds for turbine systems are disclosed. The turbine shrouds may include a unitary body including a forward and aft end, an outer surface facing a cooling chamber formed between the unitary body and a turbine casing of the turbine system, and an inner surface facing a hot gas flow path. The shrouds may also include a first cooling passage extending within the unitary body, and a plurality of impingement openings formed through the outer surface of the unitary body to fluidly couple the first cooling passage to the cooling chamber. Additionally, the shrouds may include a second cooling passage and/or a third cooling passage. The second cooling passage may extend adjacent the forward end and may be in fluid communication with the first cooling passage. The third cooling passage may extend adjacent the aft end, and may be in fluid communication with the first cooling passage.
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公开(公告)号：US10738651B2
公开(公告)日：2020-08-11
申请号：US15995085
申请日：2018-05-31
Applicant: General Electric Company
Inventor： Brad Wilson VanTassel , Joseph Anthony Weber , Bryan David Lewis , Travis J Packer
Abstract: A turbine that includes an inner shroud segment having a cooling configuration in which interior channels are configured to receive and direct a coolant. The cooling configuration may include a pair of counterflowing crossflow channels in which a first crossflow channel extends side-by-side with a neighboring second crossflow channel; and a feed and outlet channel configuration comprising neighboring feed and outlet channels. The feed channel may connect at a first connection to an upstream end of the first crossflow channel and the outlet channel may connect at a second connection to a downstream end of the second crossflow channel. The feed channel may extend in an inner radial direction from an inlet to the first connection. The outlet channel may extend in an outer radial direction from the second connection to an outlet. The feed channel may include a section that undercuts the outlet channel.
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