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公开(公告)号：US20190368364A1
公开(公告)日：2019-12-05
申请号：US15995082
申请日：2018-05-31
Applicant: General Electric Company
Inventor： Brad Wilson VanTassel , Steven Paul Byam , Joseph Anthony Weber , Evan Andrew Sewall , Travis J. Packer
Abstract: A turbine of a gas turbine engine that includes a stationary shroud ring having inner shroud segments circumferentially stacked about a hot gas path. The inner shroud segments may include a first inner shroud segment that includes: a cooling configuration having cooling channels configured to receive and direct a coolant through an interior of the first inner shroud segment, where each of the cooling channels extends lengthwise between a first end and a second end that includes an outlet formed through an exterior surface of the first inner shroud segment; a circumferential edge; a slot formed in the circumferential edge; and a sealing member positioned within the slot. The outlet of at least one of the cooling channels may be positioned within the slot.
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公开(公告)号：US10458342B2
公开(公告)日：2019-10-29
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.
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公开(公告)号：US10378383B2
公开(公告)日：2019-08-13
申请号：US15416038
申请日：2017-01-26
Applicant: General Electric Company
Inventor： Martin James Jasper , Ajay Gangadhar Patil , Brad Wilson VanTassel
Abstract: Various embodiments of the disclosure include an alignment apparatus for assembly alignment and load sharing. The alignment apparatus may include: an alignment pin including a first end and an opposing, second end, wherein the first end is configured to couple with a first hole in a first turbine nozzle diaphragm and the second end is configured to couple with a second hole in a second, adjacent turbine nozzle diaphragm. Embodiments of the disclosure may also include a turbine and a combined-cycle power plant. The turbine may include: a first nozzle diaphragm; and a second, adjacent nozzle diaphragm, wherein the first diaphragm is directly coupled to the second diaphragm. The combined-cycle power plant may include: a steam turbine; a gas turbine; a first nozzle diaphragm within the gas turbine; a second, adjacent nozzle diaphragm within the gas turbine; and an alignment pin coupling the first diaphragm directly to the second diaphragm.
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公开(公告)号：US20170167283A1
公开(公告)日：2017-06-15
申请号：US14963735
申请日：2015-12-09
Applicant: General Electric Company
CPC classification number: F01D11/005 , F01D25/005 , F01D25/24 , F05D2220/32 , F05D2240/11 , F05D2240/128 , F05D2240/14 , F05D2240/55 , F05D2240/57 , F05D2300/502 , F16J15/0825 , F16J15/0887
Abstract: Various embodiments include gas turbine seals and methods of forming such seals. In some cases, a turbine includes: a first arc segment adjacent to a second arc segment, each arc segment including an end surface and radially facing surfaces extending from opposite ends of the end surface; a slot located between the end surfaces of the first arc segment and the second arc segment; and a first seal disposed in the slot, the first seal contacting the first arc segment at the end surface and extending over the radially facing surfaces of the first arc segment, the first seal including: a shim contacting the first arc segment; a laminate material over the shim and covering the shim; and a conforming material coupling the laminate material to the shim.
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公开(公告)号：US20140147283A1
公开(公告)日：2014-05-29
申请号：US13685950
申请日：2012-11-27
Applicant: GENERAL ELECTRIC COMPANY
Inventor： John David Ward, Jr. , Kelvin Rono Aaron , James Ryan Connor , Melbourne James Myers , Brad Wilson VanTassel
CPC classification number: F01D5/005 , F01D5/225 , F05D2230/80 , F05D2240/307 , F05D2260/94 , F05D2260/941 , F05D2270/332 , Y10T29/49234 , Y10T83/04
Abstract: According to one aspect of the invention, a method is provided for modifying an airfoil shroud located at a tip of an airfoil of a 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 being proximate a seal rail extending circumferentially from the substantially horizontal surface and forming a relief cut in the airfoil shroud to remove the reference location, wherein a modifying of the airfoil shroud is complete following forming of the relief cut.
Abstract translation: 根据本发明的一个方面，提供了一种用于修改位于翼型的翼型的尖端处的翼型护罩的方法，所述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，参考位置靠近从基本水平的表面周向延伸的密封轨道，并在翼型护罩中形成浮雕切口以移除参考位置，其中修改 的翼型护罩在形成浮雕切割后完成。
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Patent Agency Ranking
公开(公告)号：US11454133B2
公开(公告)日：2022-09-27
申请号：US16663912
申请日：2019-10-25
Applicant: General Electric Company
Inventor： Matthew Troy Hafner , Brad Wilson VanTassel , Christopher Donald Porter , Srikanth Chandrudu Kottilingam
Abstract: An embodiment of an independent cooling circuit for selectively delivering cooling fluid to a component of a gas turbine system includes: a plurality of independent circuits of cooling channels embedded within an exterior wall of the component, wherein the plurality of circuits of cooling channels are interwoven together; an impingement plate; and a plurality of feed tubes connecting the impingement plate to the exterior wall of the component and fluidly coupling each of the plurality of circuits of cooling channels to at least one supply of cooling fluid, wherein, in each of the plurality of circuits of cooling channels, the cooling fluid flows through the plurality of feed tubes into the circuit of cooling channels only in response to a formation of a breach in the exterior wall of the component that exposes at least one of the cooling channels of the circuit of cooling channels.
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公开(公告)号：US11434767B2
公开(公告)日：2022-09-06
申请号：US16663941
申请日：2019-10-25
Applicant: General Electric Company
Inventor： Matthew Troy Hafner , Lyndsay Marie Kibler , Brad Wilson VanTassel , Benjamin Paul Lacy , Zachary John Snider , Christopher Donald Porter , Srikanth Chandrudu Kottilingam
Abstract: An embodiment of an independent cooling circuit for selectively delivering cooling fluid to a component of a gas turbine system includes: at least one coolant feed channel fluidly coupled to a supply of cooling fluid; and an interconnected circuit of cooling channels, including: an interconnected circuit of cooling channels embedded within an exterior wall of the component; an impingement plate; and a plurality of feed tubes connecting the impingement plate to the exterior wall of the component and fluidly coupling a supply of cooling fluid to the interconnected circuit of cooling channels; wherein the cooling fluid flows through the plurality of feed tubes into the interconnected circuit of cooling channels only in response to a formation of a breach in the exterior wall of the component that exposes at least one of the cooling channels.
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公开(公告)号：US11242760B2
公开(公告)日：2022-02-08
申请号：US16749143
申请日：2020-01-22
Applicant: General Electric Company
Inventor： Zachary John Snider , Brad Wilson VanTassel , Jeffrey Clarence Jones
IPC: F01D5/18
Abstract: A turbine rotor blade is additively manufactured and includes an airfoil body with a radially extending chamber for receiving a coolant flow, a tip end at a radial outer end of the airfoil body, and a shank at a radial inner end of the airfoil body. The radially extending chamber extends at least partially into the shank to define a shank inner surface. An integral impingement cooling structure is within the radially extending chamber. The integral impingement cooling structure allows an exterior surface of a hollow body thereof to be uniformly spaced from the airfoil inner surface despite the curvature of the chamber. The turbine rotor blade has impingement cooling throughout the blade.
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公开(公告)号：US11162432B2
公开(公告)日：2021-11-02
申请号：US16575785
申请日：2019-09-19
Applicant: General Electric Company
Inventor： Travis J Packer , Brad Wilson VanTassel , William Scott Zemitis
Abstract: A vane of a turbine system is provided. The vane includes: an internal cavity configured to receive a flow of cooling fluid; a variable thickness wall adjacent the internal cavity; and an impingement plate separating the variable thickness wall from the internal cavity, the impingement plate including a plurality of apertures for directing the cooling fluid into an impingement cavity and against the variable thickness wall, wherein the impingement plate is configured to follow a contour of the variable thickness wall.
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公开(公告)号：US20210123348A1
公开(公告)日：2021-04-29
申请号：US16663941
申请日：2019-10-25
Applicant: General Electric Company
Inventor： Matthew Troy Hafner , Lyndsay Marie Kibler , Brad Wilson VanTassel , Benjamin Paul Lacy , Zachary John Snider , Christopher Donald Porter , Srikanth Chandrudu Kottilingam
IPC: F01D5/18
Abstract: An embodiment of an independent cooling circuit for selectively delivering cooling fluid to a component of a gas turbine system includes: at least one coolant feed channel fluidly coupled to a supply of cooling fluid; and an interconnected circuit of cooling channels, including: an interconnected circuit of cooling channels embedded within an exterior wall of the component; an impingement plate; and a plurality of feed tubes connecting the impingement plate to the exterior wall of the component and fluidly coupling a supply of cooling fluid to the interconnected circuit of cooling channels; wherein the cooling fluid flows through the plurality of feed tubes into the interconnected circuit of cooling channels only in response to a formation of a breach in the exterior wall of the component that exposes at least one of the cooling channels.
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