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公开(公告)号：US11952918B2
公开(公告)日：2024-04-09
申请号：US17868911
申请日：2022-07-20
Applicant: General Electric Company
Inventor： Matthew Troy Hafner , John M. Matthews , Zachary John Snider
CPC classification number: F01D9/044 , F01D5/187 , F01D5/188 , F01D5/189 , F01D9/041 , F05D2230/237 , F05D2240/81 , F05D2260/201 , F05D2260/2214
Abstract: A stator vane includes a platform that defines an opening. The stator vane further includes an airfoil that has a leading edge, a trailing edge, a suction side wall, and a pressure side wall. The airfoil extends radially between a base and a tip. At least one of the base or the tip includes a protrusion. The protrusion extends into the opening of the platform such that the platform surrounds the protrusion of the airfoil. The stator vane further includes a braze joint disposed between and fixedly coupling the platform and the protrusion of the airfoil. The stator vane further includes a cooling circuit defined in at least one of the protrusion or the platform to cool the braze joint.
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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：US11333024B2
公开(公告)日：2022-05-17
申请号：US16656650
申请日：2019-10-18
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Sandip Dutta , James Zhang , Gary Michael Itzel , John McConnell Delvaux , Matthew Troy Hafner
Abstract: A turbine component includes a root and an airfoil extending from the root to a tip opposite the root. The airfoil forms a leading edge and a trailing edge portion extending to a trailing edge. Radial cooling channels in the trailing edge portion of the airfoil permit radial flow of a cooling fluid through the trailing edge portion. Each radial cooling channel has a first end at a lower surface at a root edge of the trailing edge portion or at an upper surface at a tip edge of the trailing edge portion and a second end opposite the first end at the lower surface or the upper surface. A method of making a turbine component and a method of cooling a turbine component are also disclosed.
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公开(公告)号：US11034842B2
公开(公告)日：2021-06-15
申请号：US16220804
申请日：2018-12-14
Applicant: General Electric Company
Inventor： Matthew Troy Hafner , John McConnell Delvaux , Jason Robert Parolini , Rajendra Kumar Bordia , Quan Li
Abstract: A coating includes: at least 34.9 percent by mass silicon dioxide; at least 9.1 percent by mass aluminum oxide; and at least 16.1 percent by mass yttrium oxide.
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Patent Agency Ranking
公开(公告)号：US20210140328A1
公开(公告)日：2021-05-13
申请号：US17151799
申请日：2021-01-19
Applicant: General Electric Company
Inventor： Matthew Troy Hafner , John McConnell Delvaux , Thomas Raymond Farrell , Markus Feigl
Abstract: A method may include: in a used metal turbomachine blade including a root including a shank, a platform coupled to the shank and an airfoil coupled to the platform, removing the airfoil, leaving a remaining base including the platform, the shank and the root. The method may also form a radially extending opening through the platform into the shank, and insert a ceramic shank nub extending from a ceramic airfoil into the radially extending opening of the remaining base. The ceramic airfoil is fixedly attached to the remaining base. The method allows reuse of the metal shank while providing the lower cooling requirements of a ceramic airfoil.
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公开(公告)号：US20210010423A1
公开(公告)日：2021-01-14
申请号：US16504865
申请日：2019-07-08
Applicant: General Electric Company
Inventor： Zachary John Snider , Matthew Troy Hafner , Lyndsay Marie Kibler
Abstract: A flow regulating system for increasing a flow of cooling fluid supplied to a cooling system of a component of a gas turbine system is provided. The flow regulating system includes: a pneumatic circuit embedded within a section of the component, the pneumatic circuit including a set of interconnected pneumatic passages; and a pressure-actuated switch fluidly coupled to the pneumatic circuit. The pressure-actuated switch is activated in response to a formation of a breach in the section of the component and an exposure of at least one of the pneumatic passages of the pneumatic circuit embedded in the section of the component. The activation of the pressure-actuated switch increases the flow of cooling fluid supplied to the cooling system of the component.
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公开(公告)号：US10851658B2
公开(公告)日：2020-12-01
申请号：US15425545
申请日：2017-02-06
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Matthew Troy Hafner
Abstract: A nozzle assembly is disclosed, including a CMC nozzle shell, a nozzle spar, and an endwall. The CMC nozzle shell includes a CMC composition and an interior cavity. The nozzle spar is partially disposed within the interior cavity and includes a metallic composition, a cross-sectional conformation, a plurality of spacers protruding from the cross-sectional conformation, the plurality of spacers contacting the CMC nozzle shell, and a spar cap. The endwall includes at least one surface in lateral contact with the spar cap and maintains a lateral orientation of the CMC nozzle shell and the nozzle spar relative to the endwall. The lateral orientation maintains a predetermined throat area of the nozzle assembly. A method for forming the nozzle assembly includes inserting the nozzle spar into the interior cavity, rotating the CMC nozzle shell and the nozzle spar laterally relative to the endwall, and maintaining the lateral orientation.
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29.发明申请公开(公告)号：US20200256204A1
公开(公告)日：2020-08-13
申请号：US16270071
申请日：2019-02-07
Applicant: General Electric Company
Inventor： Matthew Troy Hafner , John McConnell Delvaux , Thomas Raymond Farrell , Markus Feigl
IPC: F01D5/30
Abstract: A method may include: in a used metal turbomachine blade including a root including a shank, a platform coupled to the shank and an airfoil coupled to the platform, removing the airfoil, leaving a remaining base including the platform, the shank and the root. The method may also form a radially extending opening through the platform into the shank, and insert a ceramic shank nub extending from a ceramic airfoil into the radially extending opening of the remaining base. The ceramic airfoil is fixedly attached to the remaining base. The method allows reuse of the metal shank while providing the lower cooling requirements of a ceramic airfoil.
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公开(公告)号：US10544701B2
公开(公告)日：2020-01-28
申请号：US15623990
申请日：2017-06-15
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Glenn Curtis Taxacher , John McConnell Delvaux , Matthew Troy Hafner
Abstract: A turbine shroud assembly is disclosed including an inner shroud, an outer shroud, a shroud dampening pin, and a biasing apparatus. The inner shroud is adjacent to a hot gas path. The outer shroud is adjacent to the inner shroud and distal from the hot gas path, and includes a channel extending from an aperture adjacent to the inner shroud. The shroud dampening pin is within the channel and contacts the inner shroud, and includes a shaft, a contact surface, and a cap. The shaft is within the channel. The contact surface extends through the aperture in contact with the inner shroud. The cap is distal across the shaft from the contact surface. The biasing apparatus contacts the cap, is driven by a pressurized fluid, and provides a biasing force away from the outer shroud along the shroud dampening pin to the inner shroud through the contact surface.
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