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公开(公告)号：US11480061B2
公开(公告)日：2022-10-25
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：US11215074B2
公开(公告)日：2022-01-04
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：US11179917B2
公开(公告)日：2021-11-23
申请号：US15401575
申请日：2017-01-09
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Matthew Troy Hafner , John McConnell Delvaux , Glenn Curtis Taxacher , Zachary John Snider
Abstract: A CMC ply assembly is disclosed including at least one matrix ply interspersed amongst a plurality of CMC plies. Each of the plurality of CMC plies includes a first matrix and a plurality of ceramic fibers. The at least one matrix ply includes a second matrix and is essentially free of ceramic fibers. The plurality of CMC plies and the at least one matrix ply are arranged in an undensified ply stack having an article conformation. A CMC article is disclosed including a plurality of densified CMC plies and at least one densified matrix ply interspersed amongst the plurality of densified CMC plies. A method for forming the CMC article is disclosed including forming, carburizing, infusing a melt infiltration agent into, and densifying the CMC ply assembly. The melt infiltration agent infuses more completely through the at least one matrix ply than through the plurality of CMC plies.
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公开(公告)号：US11035247B2
公开(公告)日：2021-06-15
申请号：US15088768
申请日：2016-04-01
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Matthew Troy Hafner , Scott Francis Johnson , James Joseph Murray
Abstract: A turbine apparatus is disclosed including a first article and a second article disposed between the first article and a hot gas path of a turbine. The first article includes at least one first article cooling channel in fluid communication with and downstream from a cooling fluid source, and the second article includes at least one second article cooling channel in fluid communication with and downstream from the at least one first article cooling channel. A method for redundant cooling of the turbine apparatus is disclosed including flowing a cooling fluid from the cooling fluid source through at least one first article cooling channel, exhausting the cooling fluid from the at least one first article cooling channel into at least one second article cooling channel, and flowing the cooling fluid through the at least one second article cooling channel.
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公开(公告)号：US11035239B2
公开(公告)日：2021-06-15
申请号：US16170794
申请日：2018-10-25
Applicant: General Electric Company
Inventor： Peter de Diego , John Ellington Greene , Matthew Troy Hafner , David Randall Hobart , James Joseph Murray, III
IPC: F01D9/04 , F01D5/28 , C04B35/565 , C04B41/50 , B32B18/00
Abstract: A ceramic matrix composite turbine nozzle includes a primary outer nozzle platform; a primary inner nozzle platform; and an airfoil-shaped body extending between the primary inner and primary outer nozzle platforms. The body includes core plies defining a cavity; composite wrap plies circumscribing the core plies and defining an airfoil shape; a secondary outer nozzle platform in contact with the primary outer nozzle platform; and a secondary inner nozzle platform in contact with the primary inner nozzle platform. Each composite wrap ply has two layers of unidirectional fibers oriented transverse to each other and has first and second longitudinal edges. The first and second longitudinal edges are cut into fingers, which are folded in a transverse direction away from a turbine nozzle longitudinal axis and are interleaved between platform plies to define the secondary inner nozzle platform and the secondary outer nozzle platform.
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Patent Agency Ranking
公开(公告)号：US10900362B2
公开(公告)日：2021-01-26
申请号：US16247327
申请日：2019-01-14
Applicant: General Electric Company
Inventor： Jonathan Dwight Berry , Matthew Troy Hafner , Russell Pierson DeForest
Abstract: An insert system for an airfoil plenum includes a first insert and a second insert that include a plurality of impingement openings defined therein. The first insert includes a forward-facing inlet opening. The second insert includes a neck portion having a radial-facing inlet opening, an aft opening, and a cavity in flow communication between the radial-facing inlet opening and the aft opening. The second insert is sized for insertion into the plenum radially through a plenum inlet such that the neck portion is positioned in the plenum inlet. The first insert is sized for insertion into the second insert radially through the radial-facing inlet opening. When the neck portion is positioned in the plenum inlet, the first insert is moveable aftward through the aft opening into an installed position such that the forward-facing inlet opening opens into the cavity.
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公开(公告)号：US10822955B2
公开(公告)日：2020-11-03
申请号：US16235114
申请日：2018-12-28
Applicant: General Electric Company
Inventor： John McConnell Delvaux , Markus Feigl , Matthew Troy Hafner , Michael Anthony Wondrasek , James Zhang , Peter de Diego
Abstract: A gas turbine that includes a rotor blade that includes an airfoil. The airfoil may include non-integral base and top portions. The airfoil may include a pin connector connecting the top portion to the base portion. The pin connector may include: a tab extending from the top portion; a complimentary slot for receiving the tab formed in the base portion; an elongated pin cavity formed through an interior region of the airfoil, where the pin cavity intersects the slot to divide the pin cavity into first and second pin cavity segments; a tab aperture formed through the tab, where the tab aperture is positioned so align with the pin cavity upon the tab being received within the slot; and a locking pin that extends continuously through the first segment of the pin cavity, the tab aperture, and the second segment of the pin cavity.
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公开(公告)号：US10808575B2
公开(公告)日：2020-10-20
申请号：US15624070
申请日：2017-06-15
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Glenn Curtis Taxacher , John McConnell Delvaux , Matthew Troy Hafner
Abstract: A turbine component assembly is disclosed, including a first component, a second component, and a circumferentially oriented flat spring. The first component is arranged to be disposed adjacent to a hot gas path, and includes a ceramic matrix composite composition. The second component is adjacent to the first component and arranged to be disposed distal from the hot gas path across the first component. The circumferentially oriented flat spring is disposed on and directly contacting the second component and directly contacting and supporting the first component as a compliant contact interface between the first component and the second component. The circumferentially oriented flat spring provides a radial spring compliance between the first component and the second component.
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公开(公告)号：US10648348B2
公开(公告)日：2020-05-12
申请号：US15623763
申请日：2017-06-15
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Matthew Troy Hafner , Joshua Lee Margolies
Abstract: A coated ceramic matrix composite component and a gas turbine assembly are provided. The coated ceramic matrix composite component comprises a substrate comprising an endface surface and a hot gas path surface. The hot gas path surface is arranged and disposed to contact a hot gas path when the component is installed in the gas turbine assembly. The endface surface is disposed at an endface angle to the hot gas path surface and opposing at least one adjacent component when the component is installed in the gas turbine assembly. The coated ceramic matrix composite component further comprises an environmental barrier coating on at least a portion of the endface surface.
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公开(公告)号：US10550721B2
公开(公告)日：2020-02-04
申请号：US15080201
申请日：2016-03-24
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Matthew Troy Hafner , Gary Michael Itzel , John McConnell Delvaux , Sandip Dutta
Abstract: An apparatus is disclosed including a first and second article, a first interface volume disposed between and enclosed by the first article and second article, a cooling fluid supply, and at least one cooling fluid channel in fluid communication with the cooling fluid supply and the first interface volume. The first article includes a first material composition. The second article includes a second material composition. The at least one cooling fluid channel includes a heat exchange portion disposed in at least one of the first and second article downstream of the cooling fluid supply and upstream of the first interface volume. A turbine shroud is disclosed wherein the first and second articles are an outer and inner shroud. A turbine nozzle is disclosed wherein the first and second articles are an endwall and fairing.
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