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公开(公告)号：US09822653B2
公开(公告)日：2017-11-21
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.
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公开(公告)号：US20170016348A1
公开(公告)日：2017-01-19
申请号：US14801187
申请日：2015-07-16
Applicant: General Electric Company
Inventor： Christopher Lee Golden , Dustin Michael Earnhardt , Michelle Jessica Iduate , Bryan David Lewis , Christopher Donald Porter , David Wayne Weber
CPC classification number: F01D9/065 , F05D2240/81 , Y02T50/676
Abstract: Embodiments of the present disclosure provide a cooling structure for a stationary blade, which can include: an endwall coupled to a radial end of an airfoil, relative to a rotor axis of a turbomachine; and a substantially crescent-shaped chamber positioned within the endwall and radially displaced from a trailing edge of the airfoil, the substantially crescent-shaped chamber receiving a cooling fluid from a cooling circuit, wherein the substantially crescent-shaped chamber extends from a fore section positioned proximal to one of a pressure side surface and a suction side surface of the airfoil to an aft section positioned proximal to the trailing edge of the airfoil and the other of the pressure side surface and the suction side surface of the airfoil, wherein the aft section of the substantially crescent-shaped chamber is in fluid communication with the fore section of the substantially crescent-shaped chamber.
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，其可以包括：相对于涡轮机的转子轴线耦合到翼型件的径向端部的端壁; 以及基本上月牙形的腔室，其定位在端壁内并且从翼型件的后缘径向偏移，基本上月牙形的腔室从冷却回路接收冷却流体，其中基本上月牙形的腔室从位于 靠近所述翼型件的压力侧表面和吸力侧表面之一到位于所述翼型件的后缘附近并且所述翼型件的所述压力侧表面和所述吸力侧表面中的另一个的后部，其中所述后部 基本上月牙形的腔室与基本上新月形的腔室的前部部分流体连通。
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公开(公告)号：US20150013345A1
公开(公告)日：2015-01-15
申请号：US13939727
申请日：2013-07-11
Applicant: General Electric Company
Inventor： Christopher Donald Porter , Gregory Thomas Foster , Aaron Ezekiel Smith , David Wayne Weber , Michelle J. Rogers
IPC: F01D25/12
CPC classification number: F01D25/12 , F01D11/24 , F05D2240/11 , F05D2260/201 , F05D2260/202 , Y02T50/676
Abstract: A shroud segment for a casing of gas turbine includes a body configured for attachment to the casing proximate a localized critical process location within the casing. The body has a leading edge, a trailing edge, and two side edges. The critical process location is located between the leading edge and the trailing edge when the body is attached to the casing. A cooling passage is defined in the body along one of the side edges with one of an inlet or an outlet proximate the critical process location. The cooling passage is configured large enough to cool the one side edge adjacent the cooling passage to a desired level during operation of the gas turbine. The critical process locations may be related to temperatures, pressures or other measurable features of the gas turbine environment when in use.
Abstract translation: 用于燃气涡轮机壳体的护罩段包括构造成用于附接到壳体内的主体，该主体靠近壳体内的局部临界过程位置。 主体具有前缘，后缘和两个侧边。 当主体连接到壳体时，临界过程位置位于前缘和后缘之间。 冷却通道在主体中沿着一个侧边缘限定，其中一个入口或出口靠近临界过程位置。 冷却通道被构造成足够大以在燃气轮机的操作期间将邻近冷却通道的一侧边缘冷却到期望的水平。 关键过程位置可能与使用中的燃气轮机环境的温度，压力或其他可测量特征有关。
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公开(公告)号：US20230142974A1
公开(公告)日：2023-05-11
申请号：US18149858
申请日：2023-01-04
Applicant: General Electric Company
Inventor： Matthew Troy Hafner , Christopher Donald Porter , Zachary John Snider , Jeffrey Clarence Jones
CPC classification number: B22F10/00 , B22F3/1007 , B22F3/24 , B33Y80/00 , B22F10/28 , B05B12/26 , B33Y10/00
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：US20220220858A1
公开(公告)日：2022-07-14
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
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: 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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Patent Agency Ranking
公开(公告)号：US20220205363A1
公开(公告)日：2022-06-30
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
IPC: F01D5/18
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：US20220118514A1
公开(公告)日：2022-04-21
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: B22F3/105 , B22F3/10 , B22F3/24 , B23K26/066
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：US20210308944A1
公开(公告)日：2021-10-07
申请号：US16837089
申请日：2020-04-01
Applicant: General Electric Company
Inventor： Travis J Packer , Brad Wilson VanTassel , Christopher Donald Porter , Jonathan Matthew Lomas , Glenn Curtis Taxacher
IPC: B29C64/286
Abstract: A mask is provided for an additively manufactured part including a plurality of spaced openings in a surface of the part. The mask is made with the part and includes an attachment ligament configured to integrally couple to the part between the openings in a cantilever fashion. First and second cover members include a proximal ends integrally coupled to the attachment ligament and distal ends extending at least partially over a respective portions of the plurality of openings. A detachment member extends from each of the first and second cover members. The attachment ligament is the sole connection to the part. The mask may have an umbrella shape in cross-section.
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公开(公告)号：US20170226878A1
公开(公告)日：2017-08-10
申请号：US15019442
申请日：2016-02-09
Applicant: General Electric Company
IPC: F01D9/04
CPC classification number: F01D9/041 , F01D5/143 , F01D5/145 , F05D2220/31 , F05D2220/32 , F05D2240/121 , F05D2240/128 , F05D2250/73 , F05D2250/74 , Y02T50/673
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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公开(公告)号：US20150211377A1
公开(公告)日：2015-07-30
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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