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公开(公告)号：US20170276359A1
公开(公告)日：2017-09-28
申请号：US15464452
申请日：2017-03-21
Applicant: General Electric Company
Inventor： Jonathan Dwight Berry , Michael John Hughes
IPC: F23R3/00
CPC classification number: F23R3/346
Abstract: The present disclosure is directed to the operation and turndown of a segmented annular combustion system. The method includes injecting, via a fuel nozzle, a combustible mixture into a primary combustion zone between an adjacent pair of integrated combustor nozzles and burning the combustible mixture. The method further includes flowing air and injecting fuel into a premixing channel defined within a first integrated combustor nozzle to produce a second combustible mixture. The second combustible mixture is injected into a secondary combustion zone where it is combusted. The flow of combustion gases is accelerated, via turbine nozzles of the integrated combustor nozzles, toward turbine blades of a downstream turbine section. The method permits turndown of the combustion system by reducing or shutting off fuel to various components of the combustion system.
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公开(公告)号：US20170276357A1
公开(公告)日：2017-09-28
申请号：US15464425
申请日：2017-03-21
Applicant: General Electric Company
Inventor： Jonathan Dwight Berry , Stanley Kevin Widener , Michael John Hughes
CPC classification number: F23R3/002 , F23R3/286 , F23R3/34 , F23R3/50 , F23R2900/03044
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. The fuel injection panel includes an aft end portion, a first side wall, a second side wall, premixing channels defined between the first side wall and the side wall, and injection outlets defined along at least one of the first side wall and the second side wall. The aft end portion defines a turbine nozzle portion. An interior portion between the first side wall and the second side wall includes walls that extend between the first and second side walls, thereby partitioning the interior portion into discrete air cavities. The air cavities and the liner segments may be cooled by impingement inserts or panels.
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公开(公告)号：US20170176014A1
公开(公告)日：2017-06-22
申请号：US14978068
申请日：2015-12-22
Applicant: General Electric Company
Inventor： Michael John Hughes , Jonathan Dwight Berry
CPC classification number: F23R3/346 , F01D5/186 , F01D5/187 , F01D9/023 , F01D9/041 , F01D9/06 , F01D25/12 , F01D25/14 , F02C3/04 , F02C7/12 , F05D2220/32 , F05D2240/123 , F05D2240/124 , F05D2240/35 , F05D2260/201 , F05D2260/202 , F23R3/10 , F23R2900/03044
Abstract: A gas turbine that includes: a combustor coupled to a turbine that define a working fluid flowpath; a compressor discharge cavity; a staged injection system that includes the forward injector and a staged injector; a stator blade positioned extending across the working fluid flowpath between an inboard sidewall and an outboard sidewall. A one-way continuous coolant flowpath that includes: an intake section that comprises an upstream port connected to the compressor discharge cavity and a downstream port formed through one of the inboard and outboard sidewalls; an outtake section that comprises a downstream port connected to the staged injector and an upstream port formed through the same one of the inboard and outboard sidewalls; and a cooling circuit extending through an interior of the airfoil of the stator blade and connecting to the downstream port of the intake section and the upstream port of the outtake section.
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公开(公告)号：US20170138595A1
公开(公告)日：2017-05-18
申请号：US14944341
申请日：2015-11-18
Applicant: General Electric Company
Inventor： Jonathan Dwight Berry , Michael John Hughes
CPC classification number: F23R3/002 , F23R3/005 , F23R3/06 , F23R2900/03043 , F23R2900/03044
Abstract: The present application provides a combustor liner for use with a gas turbine engine. The combustor liner may include a liner wall extending from a head end to an aft end in whole or in part, a number of liner wall cooling channels positioned within the liner wall and extending from an inlet to an outlet, and a number of liner return ducts. The outlets of the liner wall cooling channels may be positioned about the liner return ducts.
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Patent Agency Ranking
公开(公告)号：US09528704B2
公开(公告)日：2016-12-27
申请号：US14186157
申请日：2014-02-21
Applicant: General Electric Company
Inventor： Michael John Hughes , Gregory Allen Boardman , Johnie Franklin McConnaughhay , Carlo Antonio Arguinzoni
Abstract: A system includes a a combustor cap configured to be coupled to a plurality of mixing tubes of a multi-tube fuel nozzle, wherein each mixing tube of the plurality of mixing tubes is configured to mix air and fuel to form an air-fuel mixture. 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. In addition, each nozzle of the multiple nozzles includes a first end and a second end. The first end is coupled to the respective mixing tube of the multiple mixing tubes. The second end defines a non-round outlet for the air-fuel mixture. Each nozzle of the multiple nozzles includes an inner surface having first and second portions, the first portion radially diverges along an axial direction from the first end to the second end, and the second portion radially converges along the axial direction from the first end to the second end.
Abstract translation: 一种系统包括：燃烧器盖，其构造成联接到多管燃料喷嘴的多个混合管，其中多个混合管的每个混合管被配置为混合空气和燃料以形成空气 - 燃料混合物。 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。 此外，多个喷嘴的每个喷嘴包括第一端和第二端。 第一端连接到多个混合管的各个混合管。 第二端限定了空气 - 燃料混合物的非圆形出口。 多个喷嘴的每个喷嘴包括具有第一和第二部分的内表面，第一部分沿着从第一端到第二端的轴向方向径向地分叉，并且第二部分沿着轴向方向从第一端径向地会聚到 第二端
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公开(公告)号：US20150241065A1
公开(公告)日：2015-08-27
申请号：US14186157
申请日：2014-02-21
Applicant: General Electric Company
Inventor： Michael John Hughes , Gregory Allen Boardman , Johnie Franklin McConnaughhay , Carlo Antonio Arguinzoni
IPC: F23R3/28
Abstract: A system includes a a combustor cap configured to be coupled to a plurality of mixing tubes of a multi-tube fuel nozzle, wherein each mixing tube of the plurality of mixing tubes is configured to mix air and fuel to form an air-fuel mixture. 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. In addition, each nozzle of the multiple nozzles includes a first end and a second end. The first end is coupled to the respective mixing tube of the multiple mixing tubes. The second end defines a non-round outlet for the air-fuel mixture. Each nozzle of the multiple nozzles includes an inner surface having first and second portions, the first portion radially diverges along an axial direction from the first end to the second end, and the second portion radially converges along the axial direction from the first end to the second end.
Abstract translation: 一种系统包括：燃烧器盖，其构造成联接到多管燃料喷嘴的多个混合管，其中多个混合管的每个混合管被配置为混合空气和燃料以形成空气 - 燃料混合物。 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。 此外，多个喷嘴的每个喷嘴包括第一端和第二端。 第一端连接到多个混合管的各个混合管。 第二端限定了空气 - 燃料混合物的非圆形出口。 多个喷嘴的每个喷嘴包括具有第一和第二部分的内表面，第一部分沿着从第一端到第二端的轴向方向径向地分叉，并且第二部分沿轴向方向从第一端径向地会聚到 第二端
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公开(公告)号：US20150241064A1
公开(公告)日：2015-08-27
申请号：US14186016
申请日：2014-02-21
Applicant: General Electric Company
IPC: F23R3/28
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：US08904748B2
公开(公告)日：2014-12-09
申请号：US13660287
申请日：2012-10-25
Applicant: General Electric Company
Inventor： Jonathan Dwight Berry , Michael John Hughes
Abstract: A system for providing hydrogen enriched fuel includes first and second gas turbines. The second gas turbine receives a portion of compressed working fluid from the first gas turbine and produces a reformed fuel, and a fuel skid provides fluid communication between a turbine in the second gas turbine and a combustor in the first gas turbine. A method for providing hydrogen enriched fuel includes diverting a portion of a first compressed working fluid from a first compressor to a second compressor and providing a second compressed working fluid from the second compressor. The method further includes mixing a fuel with the second compressed working fluid in a reformer to produce a reformed fuel, flowing the reformed fuel through a second turbine to cool the reformed fuel, and connecting the second turbine to the second compressor so that the second turbine drives the second compressor.
Abstract translation: 一种用于提供富氢燃料的系统包括第一和第二燃气轮机。 第二燃气轮机从第一燃气轮机接收压缩的工作流体的一部分并产生重整的燃料，并且燃料滑道提供第二燃气轮机中的涡轮与第一燃气轮机中的燃烧器之间的流体连通。 提供富氢燃料的方法包括将第一压缩工作流体的一部分从第一压缩机转向第二压缩机，并从第二压缩机提供第二压缩工作流体。 该方法还包括在重整器中将燃料与第二压缩工作流体混合以产生重整燃料，使重整燃料流过第二涡轮以冷却重整燃料，并将第二涡轮连接到第二压缩机，使得第二涡轮 驱动第二压缩机。
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公开(公告)号：US20130047628A1
公开(公告)日：2013-02-28
申请号：US13660287
申请日：2012-10-25
Applicant: General Electric Company
Inventor： Jonathan Dwight Berry , Michael John Hughes
IPC: F02C3/20
Abstract: A system for providing hydrogen enriched fuel includes first and second gas turbines. The second gas turbine receives a portion of compressed working fluid from the first gas turbine and produces a reformed fuel, and a fuel skid provides fluid communication between a turbine in the second gas turbine and a combustor in the first gas turbine. A method for providing hydrogen enriched fuel includes diverting a portion of a first compressed working fluid from a first compressor to a second compressor and providing a second compressed working fluid from the second compressor. The method further includes mixing a fuel with the second compressed working fluid in a reformer to produce a reformed fuel, flowing the reformed fuel through a second turbine to cool the reformed fuel, and connecting the second turbine to the second compressor so that the second turbine drives the second compressor.
Abstract translation: 一种用于提供富氢燃料的系统包括第一和第二燃气轮机。 第二燃气轮机从第一燃气轮机接收压缩的工作流体的一部分并产生重整的燃料，并且燃料滑道提供第二燃气轮机中的涡轮与第一燃气轮机中的燃烧器之间的流体连通。 提供富氢燃料的方法包括将第一压缩工作流体的一部分从第一压缩机转向第二压缩机，并从第二压缩机提供第二压缩工作流体。 该方法还包括在重整器中将燃料与第二压缩工作流体混合以产生重整燃料，使重整燃料流过第二涡轮以冷却重整燃料，并将第二涡轮连接到第二压缩机，使得第二涡轮 驱动第二压缩机。
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