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公开(公告)号：US20170276363A1
公开(公告)日：2017-09-28
申请号：US15464443
申请日：2017-03-21
Applicant: General Electric Company
Inventor： Jonathan Dwight Berry , Michael John Hughes , Kevin Weston McMahan
IPC: F23R3/28
Abstract: A segmented annular combustion system includes integrated combustor nozzles, each of which has a fuel injection panel disposed radially between an inner liner segment and an outer liner segment. An aft end portion of the fuel injection panel defines a turbine nozzle. One or more hook plates attached to the outer surfaces of the liner segments are used to mount the integrated combustor nozzle to an inner mounting ring or an outer mounting ring. A mounting strut or mounting tenon(s) attached to the liner segments may also be employed.
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公开(公告)号：US20170276360A1
公开(公告)日：2017-09-28
申请号：US15464406
申请日：2017-03-21
Applicant: General Electric Company
Inventor： Jonathan Dwight Berry , Michael John Hughes , James Scott Flanagan
IPC: F23R3/28
CPC classification number: F23R3/28 , F23R3/286 , F23R3/46 , F23R2900/00001
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：US09435540B2
公开(公告)日：2016-09-06
申请号：US14102846
申请日：2013-12-11
Applicant: General Electric Company
Inventor： Jonathan Dwight Berry , Michael John Hughes , Kara Johnston Edwards
CPC classification number: F23R3/286 , F02C7/222 , F05D2220/32 , F23R3/343 , F23R2900/03343
Abstract: An apparatus for injecting premixed fuel and air through a center body and into the combustion zone of a gas turbine includes a fuel injector nozzle with a premix pilot nozzle having a plurality of premix passages in fluid communication with an air supply and a fuel supply that premixes air and fuel within the premix passages. The apparatus has either an active or passive fuel feed control. Fuel can be fed to the apparatus either conventionally or as a breech load circuit integrated into the oil cartridge. Fuel can be supplied passively via a fuel channel connecting the swozzle fuel plenum to the premix passages. Alternatively, fuel can be injected from the oil cartridge into the premix passages.
Abstract translation: 用于将预混合燃料和空气通过中心体注入燃气轮机的燃烧区域的装置包括具有预混合引燃喷嘴的燃料喷射器喷嘴，该预混合引燃喷嘴具有与空气源流体连通的多个预混合通道和预混合 空气和燃料在预混通道内。 该装置具有主动或被动燃料供给控制。 燃料可以传统地或作为集成到油盒中的后膛负载回路供给到设备。 燃料可以通过将喷嘴燃料增压室连接到预混通道的燃料通道被动地供给。 或者，可以将燃料从油盒注入预混通道。
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公开(公告)号：US20140000263A1
公开(公告)日：2014-01-02
申请号：US14015322
申请日：2013-08-30
Applicant: General Electric Company
Inventor： Jonathan Dwight Berry , Kevin Weston McMahan , Carl Robert Barker
IPC: F23R3/10
Abstract: A system comprising a fuel nozzle. The fuel nozzle includes a mounting base and an inlet flow conditioner extending directly from the mounting base in a downstream direction. Moreover, the inlet flow conditioner structurally supports the fuel nozzle without a central support member extending directly from the mounting base inside the inlet flow conditioner.
Abstract translation: 一种包括燃料喷嘴的系统。 燃料喷嘴包括安装基座和沿着下游方向从安装基座直接延伸的入口流动调节器。 此外，入口流动调节器结构地支撑燃料喷嘴，而没有直接从入口流动调节器内的安装基座延伸的中心支撑构件。
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公开(公告)号：US20130255273A1
公开(公告)日：2013-10-03
申请号：US13909297
申请日：2013-06-04
Applicant: General Electric Company
Inventor： Jonathan Dwight Berry , Geoffrey David Myers
IPC: F02C9/52
CPC classification number: F02C9/52 , F02C7/222 , F02C9/54 , F23R3/005 , F23R3/10 , F23R3/26 , F23R2900/03044
Abstract: A gas turbine system includes a compressor operative to output an airstream and a diffuser having an inlet to receive the airstream and an outlet to output the airstream. The outlet has an area larger than the inlet to diffuse the airstream. The gas turbine system also includes a fuel nozzle operative to receive fuel and emit the fuel in a combustor and at least one bleed duct having an inlet between the compressor and the outlet of the diffuser. The at least one bleed duct is operative to direct bleed air from downstream of the compressor to the fuel nozzle.
Abstract translation: 燃气轮机系统包括可操作地输出气流的压缩机和具有用于接收空气流的入口和用于输出气流的出口的扩散器。 出口的面积大于入口以扩散气流。 燃气轮机系统还包括燃料喷嘴，其操作用于接收燃料并在燃烧器中排放燃料，以及至少一个泄放管道，其具有在压缩机和扩散器的出口之间的入口。 至少一个排放管道可操作以将排出空气从压缩机的下游引导到燃料喷嘴。
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Patent Agency Ranking
公开(公告)号：US12050062B2
公开(公告)日：2024-07-30
申请号：US17494880
申请日：2021-10-06
Applicant: General Electric Company
Inventor： Jonathan Dwight Berry , Elizabeth Iola Paasche
CPC classification number: F28D1/0308 , F28F13/12 , F23R3/14 , F23R3/283 , F23R3/286 , F28D2021/0021 , F28D2021/0026
Abstract: Stacked cooling assemblies and combustor bead ends are provided. A stacked cooling assembly includes an inlet plate defining an inlet to a coolant circuit, an outlet plate defining an outlet of the coolant circuit, and an intermediate plate disposed between the inlet plate and die outlet plate. The intermediate plate defines an intermediate cavity. A downstream surface of the inlet plate, an upstream surface of the outlet plate, and the intermediate cavity collectively define a connecting channel that fluidly couples the inlet to the outlet.
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公开(公告)号：US20230408092A1
公开(公告)日：2023-12-21
申请号：US17007089
申请日：2020-08-31
Applicant: General Electric Company
CPC classification number: F23R3/283 , F02C7/12 , F02C7/22 , F23R2900/03044 , F23R2900/00018
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：US20230375177A1
公开(公告)日：2023-11-23
申请号：US17007060
申请日：2020-08-31
Applicant: General Electric Company
Inventor： Jonathan Dwight Berry , Michael John Hughes
IPC: F23R3/28
CPC classification number: F23R3/283 , 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 aft end portion of the combustion liner defines a turbine nozzle. The combustion liner defines a cavity forward of the turbine nozzle. The cavity extends between the first side wall and the second side wall. 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 configured to direct coolant to impinge upon the first side wall and the second side wall. Each impingement member extends from a respective inlet defined within the flange to a respective closed end. A plurality of impingement apertures are defined on each impingement member.
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49.发明授权公开(公告)号：US11519288B2
公开(公告)日：2022-12-06
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：US11434772B2
公开(公告)日：2022-09-06
申请号：US17036859
申请日：2020-09-29
Applicant: General Electric Company
Inventor： Clay Thomas Griffis , Jonathan Dwight Berry
IPC: F01D9/02 , F01D5/18 , B22F3/10 , B33Y80/00 , B33Y10/00 , B22F10/28 , B22F10/40 , B22F10/00 , B22F5/04
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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