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公开(公告)号：US11660673B2
公开(公告)日：2023-05-30
申请号：US17073565
申请日：2020-10-19
Applicant: General Electric Company
Inventor： Matthew Troy Hafner , Christopher Donald Porter , Zachary John Snider , Jeffrey Clarence Jones
IPC: B33Y80/00 , B05B12/26 , B22F10/00 , B22F3/10 , B22F3/24 , B22F10/28 , B33Y10/00 , B33Y40/20 , B22F10/47 , F01D5/28
CPC classification number: B22F10/00 , B05B12/26 , B22F3/1007 , B22F3/24 , B22F10/28 , B33Y80/00 , B22F10/47 , B22F2003/1046 , B22F2003/242 , B22F2201/03 , B22F2201/10 , B23P2700/06 , B33Y10/00 , B33Y40/20 , F01D5/288
Abstract: An additively manufactured (AM) object may include a body including an opening in an exterior surface thereof, the opening having a shape and a first area at the exterior surface of the body. A mask may be positioned over the opening. The mask has the shape of the opening and a second area that is larger than the first area so as to overhang the exterior surface of the body about the opening. A plurality of support ligaments couple to the mask and the exterior surface of the body at a location adjacent to the opening to support a portion of the mask. A coating can be applied to the object, and the mask removed. The final AM object includes a plurality of ligament elements extending from the exterior surface of the body and through the coating adjacent the opening, each ligament element at least partially surrounded by the coating.
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公开(公告)号：US11480070B2
公开(公告)日：2022-10-25
申请号：US16663873
申请日：2019-10-25
Applicant: General Electric Company
Inventor： Matthew Troy Hafner , Brad Wilson VanTassel , Christopher Donald Porter , Srikanth Chandrudu Kottilingam
Abstract: A coolant delivery system for a component of a gas turbine system includes: a plurality of independent circuits of cooling channels embedded within an exterior wall of the component, each independent circuit of cooling channels including a plurality of headers and a plurality of feed tubes fluidly coupling the plurality of headers to a supply of cooling fluid; and an impingement plate connected to the exterior wall of the component by the plurality of feed tubes of the independent circuits of cooling channels, wherein, in each of the plurality of independent circuits of cooling channels, the cooling fluid flows through the plurality of feed tubes and the plurality of headers 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：US20210348513A1
公开(公告)日：2021-11-11
申请号：US16870234
申请日：2020-05-08
Applicant: General Electric Company
Inventor： Jeffrey Clarence Jones , Zachary John Snider , Christopher Donald Porter , Brad Wilson VanTassel
Abstract: A conforming coating mask is used with a turbine component having a plurality of cooling holes. The conforming coating mask includes at least two anchors; a plurality of radial mask strips integrally formed with and extending between each of the at least two anchors; and at least one coating mask securing insert. Each at least one coating mask securing insert integrally formed with a respective at least one radial mask strip; wherein the plurality of radial mask strips align with and cover the plurality of cooling holes.
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公开(公告)号：US20170016338A1
公开(公告)日：2017-01-19
申请号：US14801197
申请日：2015-07-16
Applicant: General Electric Company
Inventor： Christopher Donald Porter , Christopher Lee Golden
CPC classification number: F01D9/041 , F01D5/187 , F01D25/12 , F05D2240/12 , F05D2240/81 , F05D2260/2214 , F05D2260/22141
Abstract: Embodiments of the present disclosure provide a cooling structure for a stationary blade. The cooling structure can include: an airfoil having a cooling circuit therein; an endwall coupled to a radial end of the airfoil; a chamber positioned within the endwall for receiving a cooling fluid from the cooling circuit, wherein the cooling fluid absorbs heat from the endwall, and a temperature of the cooling fluid in an upstream region is lower than a temperature of the cooling fluid in a downstream region; a first passage within the endwall fluidly connecting the upstream region of the chamber to a wheel space positioned between the endwall and the turbine wheel; and a second passage within the endwall fluidly connecting the downstream region of the chamber to the wheel space.
Abstract translation: 本公开的实施例提供了一种用于固定叶片的冷却结构。 冷却结构可以包括：其中具有冷却回路的翼型件; 连接到所述翼型件的径向端部的端壁; 位于端壁内的室，用于从冷却回路接收冷却流体，其中冷却流体从端壁吸收热量，并且上游区域中的冷却流体的温度低于下游区域中的冷却流体的温度 ; 所述端壁内的第一通道将所述腔室的上游区域流体连接到位于所述端壁与所述涡轮机叶轮之间的车轮空间; 以及端壁内的第二通道，其将腔室的下游区域流体连接到车轮空间。
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公开(公告)号：US09416675B2
公开(公告)日：2016-08-16
申请号：US14164707
申请日：2014-01-27
Applicant: General Electric Company
Inventor： Benjamin Paul Lacy , Srikanth Chandrudu Kottilingam , Christopher Donald Porter , David Edward Schick , David Wayne Weber
CPC classification number: F01D11/005 , F01D9/023 , F01D11/003 , F05D2240/11 , F05D2240/55 , F16J15/02 , F16J15/061 , F16J15/126
Abstract: Sealing device for providing seals between adjacent components, and turbomachines utilizing such sealing devices, are provided. A sealing device includes a seal plate insertable between the adjacent components, the seal plate comprising a first face and an opposing second face. The sealing device further includes a plurality of pins extending from one of the first face or the second face, the plurality of pins configured to space the one of the first face or the second face from contact surfaces of the adjacent components.
Abstract translation: 提供了用于在相邻部件之间提供密封的密封装置，以及利用这种密封装置的涡轮机。 密封装置包括可插入相邻部件之间的密封板，密封板包括第一面和相对的第二面。 所述密封装置还包括从所述第一面或所述第二面中的一个延伸的多个销，所述多个销用于将所述第一面或所述第二面中的一个从所述相邻部件的接触表面间隔开。
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Patent Agency Ranking
公开(公告)号：US10443437B2
公开(公告)日：2019-10-15
申请号：US15342185
申请日：2016-11-03
Applicant: General Electric Company
Inventor： Benjamin Paul Lacy , Christopher Donald Porter , David Edward Schick , Lyndsay Marie Kibler
Abstract: A cooled structure of a gas turbine engine has a main body with a leading edge, a trailing edge, a first side portion, a second side portion, and a cavity. A first set of cooling air micro-channels extends from the cavity and is arranged along the first side portion. A second set of cooling air micro-channels extends from the cavity and is arranged along the second side portion. The first and second set of cooling air micro-channels have turning portions positioned adjacent each other and interwoven exhaust ends originating from each opposing side micro-channel. Each interwoven exhaust end extends around the opposing turning portion and is configured to exhaust cooling air from a plurality of exhaust ports positioned generally radially outward from the turning portions.
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公开(公告)号：US10322575B2
公开(公告)日：2019-06-18
申请号：US15661126
申请日：2017-07-27
Applicant: General Electric Company
Inventor： Benjamin Paul Lacy , Srikanth Chandrudu Kottilingam , Christopher Donald Porter , David Edward Schick
Abstract: Various embodiments of the disclosure include a turbomachine component. and methods of forming such a component. Some embodiments include a turbomachine component including: a first portion including at least one of a stainless steel or an alloy steel; and a second portion joined with the first portion, the second portion including a nickel alloy including an arced cooling feature extending therethrough, the second portion having a thermal expansion coefficient substantially similar to a thermal expansion coefficient of the first portion, wherein the arced cooling feature is located within the second portion to direct a portion of a coolant to a leakage area of the turbomachine component.
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公开(公告)号：US10161255B2
公开(公告)日：2018-12-25
申请号：US15019442
申请日：2016-02-09
Applicant: General Electric Company
Abstract: Various embodiments of the invention include turbine nozzles and systems employing such nozzles. Various particular embodiments include a turbine nozzle having: an airfoil having: a suction side; a pressure side opposing the suction side; a leading edge spanning between the pressure side and the suction side; and a trailing edge opposing the leading edge and spanning between the pressure side and the suction side; and at least one endwall connected with the airfoil along the suction side, pressure side, trailing edge and the leading edge, the at least one endwall including a non-axisymmetric contour proximate a junction between the endwall and the leading edge of the airfoil.
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29.发明申请公开(公告)号：US20180223673A1
公开(公告)日：2018-08-09
申请号：US15426484
申请日：2017-02-07
Applicant: General Electric Company
Inventor： Benjamin Paul Lacy , Christopher Donald Porter , Ibrahim Sezer , James William Vehr
CPC classification number: F01D5/186 , F02C7/18 , F05D2250/232 , F05D2250/323 , F05D2250/324 , F05D2260/202 , Y02T50/676 , Y02T50/6765
Abstract: A hot gas path component may include a body, and a passage for delivering a coolant extending through at least a part of the body to an exit area of the body. A metering structure may be in fluid communication with the passage and disposed upstream of the exit area. The metering structure may include a converging passage portion followed by a diverging passage portion.
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公开(公告)号：US09757936B2
公开(公告)日：2017-09-12
申请号：US14584442
申请日：2014-12-29
Applicant: General Electric Company
Inventor： Benjamin Paul Lacy , Srikanth Chandrudu Kottilingam , Christopher Donald Porter , David Edward Schick
CPC classification number: B33Y80/00 , B22F3/1055 , B22F5/009 , B22F7/062 , B22F2999/00 , B33Y10/00 , F01D5/225 , F01D11/24 , F01D25/12 , F05D2230/31 , F05D2230/51 , F05D2240/11 , F05D2240/81 , F05D2260/202 , Y02P10/295 , B22F2203/05
Abstract: Various embodiments of the disclosure include a turbomachine component. and methods of forming such a component. Some embodiments include a turbomachine component including: a first portion including at least one of a stainless steel or an alloy steel; and a second portion joined with the first portion, the second portion including a nickel alloy including an arced cooling feature extending therethrough, the second portion having a thermal expansion coefficient substantially similar to a thermal expansion coefficient of the first portion, wherein the arced cooling feature is located within the second portion to direct a portion of a coolant to a leakage area of the turbomachine component.
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