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公开(公告)号：US20150027126A1
公开(公告)日：2015-01-29
申请号：US13949640
申请日：2013-07-24
Applicant: General Electric Company
Inventor： Jonathan Dwight Berry
Abstract: A fuel supply system for a gas turbine combustor includes an annular duct that at least partially defines a hot gas path within the combustor. An orifice is at least partially defined by the annular duct and defines a flow path through the annular duct into the hot gas path. A plurality of fuel injectors are arranged circumferentially around the annular duct to provide for fluid communication through the annular duct into the hot gas path. A fuel distribution manifold is disposed adjacent to an outer side of the annular duct. The fuel distribution manifold includes a main body that at least partially defines an inlet for receiving fuel, an outlet that is in fluid communication with the fuel injectors, and a fuel purge passage that provides for fluid communication between the inlet and the orifice.
Abstract translation: 用于燃气轮机燃烧器的燃料供应系统包括至少部分地限定燃烧器内的热气体通道的环形管道。 孔口至少部分地由环形管道限定，并且限定通过环形管道进入热气路径的流动路径。 多个燃料喷射器周向地设置在环形管道周围，以提供通过环形管道流入热气路径的流体连通。 燃料分配歧管邻近环形管道的外侧设置。 燃料分配歧管包括主体，其至少部分地限定用于接收燃料的入口，与燃料喷射器流体连通的出口以及提供入口和孔口之间的流体连通的燃料吹扫通道。
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公开(公告)号：US11994293B2
公开(公告)日：2024-05-28
申请号：US17007089
申请日：2020-08-31
Applicant: General Electric Company
CPC classification number: F23R3/06 , F01D9/023 , F02C3/14 , F23R3/002 , F23R3/10 , F05D2260/201 , F23R2900/03044
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 integrated combustor nozzle further includes an impingement cooling apparatus positioned within the cavity. The impingement cooling apparatus includes a flange. The impingement cooling apparatus further includes a plurality of impingement members that each extend from a respective opening defined in the flange to a respective closed end. Each impingement member defines a plurality of impingement apertures that direct air to impinge upon one of the first side wall and the second side wall. The impingement cooling apparatus further includes stand-offs extending from each impingement member of the plurality of impingement members. The stand-offs space apart each impingement member of the plurality of impingement members from surrounding surfaces.
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公开(公告)号：US11773739B2
公开(公告)日：2023-10-03
申请号：US17358691
申请日：2021-06-25
Applicant: General Electric Company
Inventor： Neelesh Nandkumar Sarawate , Jonathan Dwight Berry , Russell Pierson DeForest , Kevin Weston McMahan , Victor John Morgan , Ibrahim Klara Sezer , Deepak Trivedi
CPC classification number: F01D11/005 , F16J15/0887 , F23R3/46 , F05D2240/35 , F05D2240/55 , F23R2900/00012
Abstract: A flexible seal for sealing between two adjacent gas turbine components includes a forward end, an aft end axially separated from the forward end, and an intermediate portion between the forward end and the aft end. The intermediate portion defines a continuous curve in the circumferential direction, such that the aft end is circumferentially offset from the forward end. In other cases, the forward and aft ends are axially, radially, and circumferentially offset from one another. A method of sealing using the flexible seal includes inserting, in an axial direction, the aft end of the flexible seal into a recess defined by respective seal slots of two adjacent gas turbine components; and pushing the flexible seal in an axial direction through the recess until the forward end is disposed within the recess.
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公开(公告)号：US11428413B2
公开(公告)日：2022-08-30
申请号：US15464406
申请日：2017-03-21
Applicant: General Electric Company
Inventor： Jonathan Dwight Berry , Michael John Hughes , James Scott Flanagan
Abstract: The present disclosure is directed to a fuel injection module for a segmented annular combustion system. The fuel injection module includes a housing body, a fuel nozzle portion, and at least one fuel injection lance. The fuel nozzle portion is fluidly coupled to a fuel nozzle plenum within the housing body, and the at least one fuel injection lance is fluidly coupled to an injector fuel plenum within the housing body. In some cases, the fuel nozzle portion is a bundled tube fuel nozzle having one or more subsets of tubes. The fuel injection lances are positioned along a radial side of the housing body or circumferentially between two subsets of tubes. Liquid fuel cartridges extend through the fuel nozzle portion, the fuel injection lances, or both.
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公开(公告)号：US20220098992A1
公开(公告)日：2022-03-31
申请号：US17036859
申请日：2020-09-29
Applicant: General Electric Company
Inventor： Clay Thomas Griffis , Jonathan Dwight Berry
Abstract: Methods of fabricating a turbomachine component and turbomachine components are provided. The method includes irradiating a layer of powder in a powder bed to form a fused region. The powder is disposed on a build plate. The method further includes a step of providing a subsequent layer of powder over the powder bed by passing a recoater arm over the powder bed from a first side of the powder bed. The method further includes repeating the irradiating and providing steps until a turbine nozzle assembly is formed on the build plate. The turbine nozzle assembly includes the turbine nozzle and a plurality of heat fins disposed within the turbine nozzle. The plurality of heat fins transfer heat away from a thermally sensitive portion of the turbine nozzle.
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Patent Agency Ranking
公开(公告)号：US20220065452A1
公开(公告)日：2022-03-03
申请号：US17007108
申请日：2020-08-31
Applicant: General Electric Company
Inventor： Jonathan Dwight Berry , Jerome Walter Goike , Clay Thomas Griffis
Abstract: An integrated combustor nozzle includes a combustion liner that extends between an inner liner segment and an outer liner segment along a radial direction. The combustion liner including a forward end portion, an aft end portion, a first side wall, and a second side wall. 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 apertures that direct coolant in discrete jets towards the exterior surface of the inner liner segment or the outer liner segment. The impingement panel includes an inlet portion that extends from the impingement plate to a collection duct. The impingement panel further includes a plurality of supports spaced apart from one another. The plurality of supports extend between, and are coupled to, the inlet portion, the collection duct, and the impingement plate
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公开(公告)号：US11255545B1
公开(公告)日：2022-02-22
申请号：US17079847
申请日：2020-10-26
Applicant: General Electric Company
Inventor： Jonathan Dwight Berry , Michael John Hughes
Abstract: Integrated combustion nozzles and turbomachines are provided. An integrated combustion nozzle includes a unified head end coupled to a combustion liner. The unified head end includes a first fuel nozzle and a second fuel nozzle disposed at a forward end portion of the combustion liner. A fuel plenum is defined between the first fuel nozzle and the second fuel nozzle. A first liner portion extends from the first fuel nozzle and into an opening of a first wall of the combustion liner such that the first liner portion forms a continuous surface with the first wall. The unified head end further includes a second liner portion that extends from the second fuel nozzle and into an opening of a second wall of the combustion liner such that the second liner portion forms a continuous surface with the second wall.
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公开(公告)号：US11248794B2
公开(公告)日：2022-02-15
申请号：US16731306
申请日：2019-12-31
Applicant: General Electric Company
Inventor： Jonathan Dwight Berry
Abstract: A fluid mixing apparatus includes mixing conduits that extend through a fluid plenum. The fluid plenum, which surrounds a first wall defining a main passage fluidly coupled to a low-pressure fluid source, is surrounded itself by a second wall defining a high-pressure plenum fluidly coupled to a high-pressure fluid source. An insulated tube disposed at the inlet of the first wall delivers a third fluid. The mixing conduits fluidly couple the high-pressure plenum to the main passage, where the high-pressure fluid is mixed with low-pressure fluid and the third fluid. Optionally, the fluid plenum may house a fourth fluid that is injected through injection holes in the mixing conduits. The fluid mixing apparatus may be used to mix one or more fuels with high- and low-pressure air in a gas turbine combustor. Alternately, the fluid mixing apparatus may mix a fluid with high- and low-pressure water streams.
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公开(公告)号：US11248531B1
公开(公告)日：2022-02-15
申请号：US17126333
申请日：2020-12-18
Applicant: General Electric Company
Inventor： Jonathan Dwight Berry
Abstract: A sealing arrangement includes a stationary component, a first slot is defined between an outer wall and a first inner wall, a second slot is defined between the outer wall and a second inner wall. A rotating component moves in a circumferential direction relative to the stationary component. The rotating component includes a tip rail. A floating seal positioned between the stationary component and the rotating component. The floating seal includes an axial member having a first arm extending into the first slot and a second arm extending into the second slot. The floating seal includes a first radial member and a second radial member that extends from the axial member. A plurality of magnets coupled to the stationary component, the rotating component, and the floating seal. The plurality of magnets is arranged such that the floating seal is contained between the stationary component and the rotating component.
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公开(公告)号：US11231175B2
公开(公告)日：2022-01-25
申请号：US16012412
申请日：2018-06-19
Applicant: General Electric Company
Inventor： Jonathan Dwight Berry , Michael John Hughes , Russell Pierson DeForest , Kevin Weston McMahan , Victor John Morgan , Ibrahim Sezer , Neelesh Nandkumar Sarawate , Deepak Trivedi
Abstract: An integrated combustor nozzle includes an inner liner segment; an outer liner segment; and a panel extending radially between the inner and outer liner segments. The panel includes a forward end, an aft end, and a side walls extending axially from the forward end to the aft end. The aft end defines a turbine nozzle having a trailing edge circumferentially offset from the forward end. The inner liner segment has a pair of sealing surfaces, each of which defines a first continuous curve in the circumferential direction. The outer liner segment has a pair of sealing surfaces, each of which defines a second continuous curve in the circumferential direction. In some instances, the curves are monotonic in the circumferential direction. A segmented annular combustor including an array of such integrated combustor nozzles is also provided.
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