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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：US09528702B2
公开(公告)日：2016-12-27
申请号：US14186016
申请日：2014-02-21
Applicant: General Electric Company
CPC classification number: F23R3/283 , F23R3/10 , F23R3/286 , Y02T50/675
Abstract: A system includes a combustor cap assembly for a multi-tube fuel nozzle. The combustor cap assembly includes a support structure defining an interior volume configured to receive an air flow. The combustor cap assembly also includes multiple mixing tubes disposed within the interior volume, wherein each mixing tube is configured to mix air and fuel to form an air-fuel mixture. The combustor cap assembly further includes a combustor cap removably coupled to the support structure. The combustor cap includes multiple nozzles integrated within the combustor cap. Each nozzle of the multiple nozzles is coupled to a respective mixing tube of the multiple mixing tubes. The combustor cap is configured to internally cool itself via one or more cooling features integrated within the combustor cap.
Abstract translation: 一种系统包括用于多管燃料喷嘴的燃烧器盖组件。 燃烧器盖组件包括限定被构造成接收空气流的内部容积的支撑结构。 燃烧器盖组件还包括设置在内部容积内的多个混合管，其中每个混合管构造成混合空气和燃料以形成空气 - 燃料混合物。 燃烧器盖组件还包括可移除地联接到支撑结构的燃烧器盖。 燃烧器盖包括集成在燃烧器盖内的多个喷嘴。 多个喷嘴的每个喷嘴连接到多个混合管的相应混合管。 燃烧器盖构造成通过集成在燃烧器盖内的一个或多个冷却特征来内部冷却自身。
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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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64.发明授权Combustor having mixing tube bundle with baffle arrangement for directing fuel 有权具有混合管束的燃烧器，其具有用于引导燃料的挡板装置公开(公告)号：US09423135B2
公开(公告)日：2016-08-23
申请号：US14085887
申请日：2013-11-21
Applicant: General Electric Company
Inventor： Michael John Hughes , Johnie Franklin McConnaughhay
Abstract: A combustor includes a tube bundle that extends radially across at least a portion of the combustor. The tube bundle includes an upstream surface axially separated from a downstream surface, and a plurality of tubes extend from the upstream surface through the downstream surface to provide fluid communication through the tube bundle. A barrier extends radially inside the tube bundle between the upstream and downstream surfaces, and a baffle extends axially inside the tube bundle between the upstream surface and the barrier.
Abstract translation: 燃烧器包括径向延伸穿过燃烧器的至少一部分的管束。 管束包括从下游表面轴向分离的上游表面，并且多个管从上游表面延伸穿过下游表面以提供通过管束的流体连通。 屏障在管束之间径向延伸在上游表面和下游表面之间，并且挡板在管束之间在上游表面和屏障之间轴向延伸。
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公开(公告)号：US20140260278A1
公开(公告)日：2014-09-18
申请号：US13833878
申请日：2013-03-15
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Michael John Hughes
IPC: F23R3/00
CPC classification number: F23R3/002 , F23R3/005 , F23R3/46 , F23R2900/03043 , F23R2900/03044
Abstract: A system for tuning a combustor of a gas turbine includes a flow sleeve having an annular main body. The main body includes an upstream end, a downstream end, an inner surface and an outer surface. A cooling channel extends along the inner surface of the main body. The cooling channel extends at least partially between the downstream end and the upstream end of the main body.
Abstract translation: 用于调节燃气涡轮机的燃烧器的系统包括具有环形主体的流动套管。 主体包括上游端，下游端，内表面和外表面。 冷却通道沿着主体的内表面延伸。 冷却通道至少部分地延伸在主体的下游端和上游端之间。
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Patent Agency Ranking
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：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：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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公开(公告)号：US10830442B2
公开(公告)日：2020-11-10
申请号：US15464400
申请日：2017-03-21
Applicant: General Electric Company
Inventor： Jonathan Dwight Berry , Stanley Kevin Widener , Michael John Hughes , James Scott Flanagan
Abstract: A segmented annular combustion system with dual fuel capability includes an alternating arrangement of fuel injection modules and integrated combustor nozzles. The fuel injection module includes a bundled tube fuel nozzle portion and fuel injection lances, which are fluidly coupled via conduits to respective fuel plenums. A liquid fuel cartridge is disposed within the bundled tube fuel nozzle portion, within one of the plurality of fuel injection lances, or within both the bundled tube fuel nozzle portion and one of the plurality of fuel injection lances. A gas turbine having the segmented annular combustion system is also provided.
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公开(公告)号：US10584880B2
公开(公告)日：2020-03-10
申请号：US15464443
申请日：2017-03-21
Applicant: General Electric Company
Inventor： Jonathan Dwight Berry , Michael John Hughes , Kevin Weston McMahan
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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