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公开(公告)号：US20170276361A1
公开(公告)日：2017-09-28
申请号：US15464411
申请日：2017-03-21
Applicant: General Electric Company
Inventor： Jonathan Dwight Berry , Michael John Hughes
IPC: F23R3/28
Abstract: The present disclosure is directed to a radially stacked fuel injection module for a segmented annular combustion system. The fuel injection module includes a bundled tube fuel nozzle portion and a plurality of fuel injection lances. In one instance, a first set of fuel injection lances and a second set of fuel injection lances share a housing with the bundled tube fuel nozzle. The first and second sets of fuel injection lances are radially stacked, each set of lances being in communication with a respective injector fuel plenum. The fuel injection lances deliver fuel to a respective premixing channel formed between the side walls of an integrated combustor nozzle, an aft end of which defines a turbine nozzle. In another instance, the bundled tube fuel nozzle may be provided as a radially inner fuel nozzle and a radially outer fuel nozzle, each with a respective bundled tube fuel plenum.
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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：US20150076251A1
公开(公告)日：2015-03-19
申请号：US13956921
申请日：2013-09-19
Applicant: General Electric Company
Inventor： Jonathan Dwight Berry
IPC: F02C7/22
Abstract: A combustion system uses a fuel nozzle with an inner wall having a fuel inlet in fluid communication with a fuel outlet in a fuel cartridge. The inner wall defines a mounting location for inserting the fuel cartridge. A pair of annular lip seals around the cartridge outer wall on both sides of the fuel outlet seals the fuel passage between the fuel inlet and the fuel outlet.
Abstract translation: 燃烧系统使用燃料喷嘴，其内壁具有与燃料盒中的燃料出口流体连通的燃料入口。 内壁限定用于插入燃料盒的安装位置。 在燃料出口两侧的盒外壁周围的一对环形唇形密封件密封在燃料入口和燃料出口之间的燃料通道。
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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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128.发明授权公开(公告)号：US08893511B2
公开(公告)日：2014-11-25
申请号：US13909297
申请日：2013-06-04
Applicant: General Electric Company
Inventor： Jonathan Dwight Berry , Geoffrey David Myers
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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129.发明申请TUBE ASSEMBLY FOR USE IN FUEL INJECTION ASSEMBLIES AND METHODS OF ASSEMBLING SAME 审中-公开用于燃油喷射装置的管组件及其组装方法公开(公告)号：US20140251483A1
公开(公告)日：2014-09-11
申请号：US13788812
申请日：2013-03-07
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Carl Robert Barker , Jonathan Dwight Berry
IPC: F16L9/00
CPC classification number: F02C7/222 , Y10T29/49826
Abstract: A tube assembly for use in a fuel injection assembly of a turbine engine is provided. The tube assembly includes a housing, and a plurality of tube assembly units positioned adjacent to one another within the housing such that each tube assembly extends along a longitudinal axis of the housing. Each tube assembly unit includes a tube, and a plurality of flanges extending radially outward from each tube, wherein flanges of adjacent tube assembly units form at least a portion of at least one wall within the housing.
Abstract translation: 提供了一种用于涡轮发动机的燃料喷射组件的管组件。 管组件包括壳体和多个管组件单元，其在壳体内彼此相邻设置，使得每个管组件沿着壳体的纵向轴线延伸。 每个管组件单元包括管和从每个管径向向外延伸的多个凸缘，其中相邻管组件单元的凸缘形成壳体内的至少一个壁的至少一部分。
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公开(公告)号：US08769956B2
公开(公告)日：2014-07-08
申请号：US14015322
申请日：2013-08-30
Applicant: General Electric Company
Inventor： Jonathan Dwight Berry , Kevin Weston McMahan , Carl Robert Barker
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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