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公开(公告)号：US11939878B1
公开(公告)日：2024-03-26
申请号：US18081924
申请日：2022-12-15
Applicant: General Electric Company
Inventor： Jonathan Dwight Berry , Emily Kaufman , Clay Thomas Griffis , Bailey Basso , Archie Lee Swanner, Jr.
Abstract: A turbomachine component is provided. The turbomachine component formed from an additive manufacturing system. The additive manufacturing system defines an axial build direction, a radial direction, and a circumferential direction. The turbomachine component includes an exterior portion. The exterior portion includes a first end wall, a second end wall, and an outer band extending axially between the first end wall and the second end wall. The turbomachine component further includes an interior portion disposed within the exterior portion. The interior portion includes a self-breaking inner band extending axially between the first end wall and the second end wall. The self-breaking inner band includes a plurality of teeth disposed between the first end wall and the second end wall.
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公开(公告)号：US11371702B2
公开(公告)日：2022-06-28
申请号：US17007068
申请日：2020-08-31
Applicant: General Electric Company
Inventor： Jonathan Dwight Berry , Michael John Hughes
Abstract: An integrated combustor nozzle includes a combustion liner that extends radially between an inner liner segment and an outer liner segment. The combustion liner includes a forward end portion, an aft end portion, a first side wall, and a second side wall. The aft end portion of the combustion liner defines a turbine nozzle. The integrated combustor nozzle further includes an impingement panel having an impingement plate disposed along an exterior surface of one of the inner liner segment or the outer liner segment. The impingement plate defines a plurality of impingement holes that direct coolant in discrete jets towards the exterior surface of the inner liner segment or the outer liner segment. The impingement panel is radially spaced from the exterior surface to form a cooling flow gap therebetween. The impingement panel includes a collection duct that extends from the impingement panel and defines a collection passage.
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3.发明申请公开(公告)号：US20220195882A1
公开(公告)日：2022-06-23
申请号：US17126301
申请日：2020-12-18
Applicant: General Electric Company
Inventor： Jonathan Dwight Berry
IPC: F01D11/14 , F16J15/3288
Abstract: Sealing arrangements and rotor assemblies are provided. A sealing arrangement includes a stationary component, a rotating component spaced apart from the stationary component. A clearance is defined between the stationary component and the rotating component. The sealing arrangement further includes a plurality of magnets embedded within the rotating component. The sealing arrangement further includes a brush seal having a frame and a plurality of magnetically responsive filaments. The plurality of magnetically responsive filaments each extending from the frame to a free end. The plurality of magnetically responsive filaments are attracted to the rotating component by the plurality of magnets. The plurality of magnetically responsive filaments at least partially covering the clearance, such that a flow of fluid across the clearance is restricted.
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公开(公告)号：US11326522B1
公开(公告)日：2022-05-10
申请号：US17136131
申请日：2020-12-29
Applicant: General Electric Company
Inventor： Jonathan Dwight Berry , Michael John Hughes
Abstract: Sealing arrangements and turbomachines are provided. A sealing arrangement for a turbomachine includes a transition duct having an upstream end and a downstream end. The transition duct includes an aft frame that circumferentially surrounds the downstream end of the transition duct. A stage one nozzle spaced apart from the aft frame and defining a gap therebetween. A sealing assembly extends across the gap. The sealing assembly includes a first seal link magnetically coupled to the aft frame. The sealing assembly further includes a second seal link magnetically coupled to the first seal link and the stage one nozzle.
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公开(公告)号：US20220099027A1
公开(公告)日：2022-03-31
申请号：US17036745
申请日：2020-09-29
Applicant: General Electric Company
Abstract: Fuel injection assemblies and combustors are provided. A fuel injection assembly includes a fuel injector having a first annular wall that about an axial centerline and extends from a primary inlet disposed at a first end to a primary outlet disposed at a second end. A second annular wall surrounds the first annular wall. A fuel plenum is defined between the first annular wall and the second annular wall. A fuel duct extends from a fuel outlet defined in the second annular wall to a fuel inlet. wherein the fuel duct is in fluid communication with the fuel plenum. The fuel duct includes a polygonal segment and a cylindrical inlet segment. The polygonal segment extends from the fuel outlet to the cylindrical inlet segment.
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Patent Agency Ranking
公开(公告)号：US11287134B2
公开(公告)日：2022-03-29
申请号：US16731207
申请日：2019-12-31
Applicant: General Electric Company
Inventor： Jonathan Dwight Berry
Abstract: A combustor may include a combustor liner and flow sleeve. A high pressure air cools an outer surface of the combustor liner via openings in the flow sleeve, creating a lower pressure air in an annulus between the combustor liner and the flow sleeve. A first fuel nozzle is positioned at a primary combustion zone, and a second fuel nozzle is positioned at a secondary combustion zone of the liner. A fuel source is configured to deliver a fuel to the fuel nozzles. The fuel nozzles produce a premixture of high pressure air and the fuel, and produce a mixture of the premixture and the lower pressure air, prior to introducing the mixture to a respective primary or secondary combustion zone of the combustor. The combustor provides improved fuel premixing and is fuel flexible, and reduces pressure drop requirements. The combustor is usable in a can, annular, or segmented annular combustor assembly.
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公开(公告)号：US11262074B2
公开(公告)日：2022-03-01
申请号：US16360177
申请日：2019-03-21
Applicant: General Electric Company
Abstract: An effusion cooling element for the surface of a hot gas path (HGP) component is disclosed. The effusion cooling element includes a coolant swirling chamber embedded within the body of the HGP component. A coolant delivery passage is in the body and configured to deliver a coolant to the coolant swirling chamber. The coolant swirling chamber imparts a centrifugal force to the coolant. An effusion opening is in the HGP surface and in fluid communication with the coolant swirling chamber, the effusion opening having a smaller width than the coolant swirling chamber. The coolant exits the effusion opening over substantially all of 360° about the effusion opening, creating a coolant film on the HGP surface.
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公开(公告)号：US11187095B1
公开(公告)日：2021-11-30
申请号：US17136140
申请日：2020-12-29
Applicant: General Electric Company
Inventor： Jonathan Dwight Berry , Michael John Hughes
Abstract: A sealing arrangement includes a first aft frame and a second aft frame neighboring one another. The first aft frame and the second aft frame each include an inner portion and an outer portion. The outer portion radially separated from the inner portion. The first aft frame and the second aft frame further include a first side portion and a second side portion that each extend radially between the inner portion and the outer portion. A circumferential gap is defined between the first side portion of the first aft frame and the second side portion of the second aft frame. The sealing arrangement further includes a side seal that extends across the circumferential gap. The side seal includes one or more magnets. The side seal is at least partially held in place by the one or more magnets.
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公开(公告)号：US11002190B2
公开(公告)日：2021-05-11
申请号：US15442203
申请日：2017-02-24
Applicant: General Electric Company
Inventor： Jonathan Dwight Berry , Michael John Hughes
Abstract: An annular combustion system includes a fuel nozzle, a panel fuel injector including a fuel plenum and at least one premixing channel therein, an inner liner having a hot side surface and a cool side surface and an outer liner having a hot side surface and a cool side surface. The inner liner, the outer liner and the panel fuel injector partially define a hot gas path downstream from the fuel nozzle. The inner liner and/or the outer liner define a plurality of micro-channel cooling passages which is disposed between the hot side surface and cool side surface of the inner liner. Each micro-channel cooling passage of the first plurality of micro-channel cooling passages is in fluid communication with an inlet hole defined along the cool side surface of the respective liner and an outlet hole.
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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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