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公开(公告)号：US10544941B2
公开(公告)日：2020-01-28
申请号：US15371308
申请日：2016-12-07
Applicant: General Electric Company
Inventor： Lucas John Stoia , Richard Martin DiCintio , Timothy James Purcell , Srikanth Chandrudu Kottilingam
Abstract: A fuel nozzle assembly includes a forward plate and an aft plate which is axially spaced from the forward plate. The aft plate includes a first side surface and a second side surface. A cooling air plenum is defined within the bundled tube fuel nozzle assembly and is at least partially defined by the aft plate. A plurality of tubes extends through the forward plate, the cooling air plenum and the aft plate. A micro-cooling channel is disposed along the second side surface of the aft plate and is in fluid communication with the cooling air plenum and is in fluid communication with an exhaust aperture. A cover plate is connected to the aft plate and covers the micro-cooling channel.
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公开(公告)号：US10415831B2
公开(公告)日：2019-09-17
申请号：US15335538
申请日：2016-10-27
Applicant: General Electric Company
Abstract: A combustor assembly includes a combustion liner defining a first radial opening, an outer sleeve that at least partially surrounds the combustion liner. The outer sleeve defines a second radial opening. A mounting body having a jacket portion and a flange portion surrounds the first radial opening and extends radially outwardly from an outer surface of the combustion liner towards the outer sleeve. The flange portion is at least partially disposed within the second radial opening. An auxiliary component extends radially within the jacket portion and includes a flange portion. The flange portion of the auxiliary component is connected to the flange portion of the mounting body via a first fastener, and the flange portion of the auxiliary component is connected to the outer sleeve via a second fastener.
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公开(公告)号：US20180209653A1
公开(公告)日：2018-07-26
申请号：US15410831
申请日：2017-01-20
Applicant: General Electric Company
Abstract: A fuel injector for a gas turbine combustor includes a fuel conduit fitting and a nozzle having an inlet portion defining a mixing chamber therein. The inlet portion includes a plurality of circumferentially-spaced vanes that define a plurality of inlet flow paths within the mixing chamber. Each vane has at least one port defined therein that is in flow communication with the fuel conduit fitting such that fuel from the fuel conduit fitting is dischargeable into at least one of the inlet flow paths via the at least one port. The resulting fuel/air mixture is delivered into a secondary combustion zone of the gas turbine combustor. A gas turbine including the fuel injector and a method of fabricating the fuel nozzle are also provided.
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公开(公告)号：US20180106163A1
公开(公告)日：2018-04-19
申请号：US15292452
申请日：2016-10-13
Applicant: General Electric Company
Inventor： Seth Reynolds Hoffman , Lucas John Stoia , Sven Georg Bethke , Richard Martin DiCintio , Jeffrey Scott LeBegue , Jayaprakash Natarajan
Abstract: A combustion liner assembly includes a combustion liner having an upstream end portion and a downstream end portion and a resonator disposed proximate to the upstream end portion of the combustion liner. The resonator includes a plurality of circumferentially spaced inlet apertures disposed along a radially outer surface of the resonator, an air chamber defined within the resonator and a plurality of outlet apertures disposed along a radially inner surface of the resonator. The plurality of inlet apertures provide for fluid flow into the air chamber and the plurality of outlet apertures provide for fluid flow out of the air chamber and into a radial flow passage defined within the combustor.
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公开(公告)号：US20180100437A1
公开(公告)日：2018-04-12
申请号：US15289242
申请日：2016-10-10
Applicant: General Electric Company
CPC classification number: F02C7/264 , F05D2220/32 , F05D2240/35 , F05D2250/185 , F05D2250/281 , F05D2260/204 , F23R3/002 , F23R2900/00018 , F23R2900/03042
Abstract: An igniter assembly and a combustor including an igniter assembly is disclosed herein. The igniter assembly comprises an igniter housing. The igniter housing includes an outer surface, a first end wall and a second end wall. The igniter assembly also includes a preformed cover plate having an inner surface that is attached to the outer surface of the igniter housing. A plurality of micro-cooling channels is formed within at least one of the inner surface of the preformed cover plate and the outer surface of the igniter housing.
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Patent Agency Ranking
公开(公告)号：US20180100436A1
公开(公告)日：2018-04-12
申请号：US15289247
申请日：2016-10-10
Applicant: General Electric Company
Abstract: An aft frame for a duct of a combustor includes a rail or radial projection that extends circumferentially around the aft frame and that defines an outer surface of the aft frame. A preformed cover plate having an inner surface is attached to the outer surface of the aft frame. A plurality of micro-cooling channels is formed within at least one of the inner surface of the preformed cover plate and the outer surface of the aft frame. The preformed cover plate extends across the plurality of micro-cooling channels.
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47.发明申请SYSTEMS AND METHODS FOR CONTROL OF COMBUSTION DYNAMICS IN COMBUSTION SYSTEM 审中-公开用于控制燃烧系统中燃烧动力学的系统和方法公开(公告)号：US20160273449A1
公开(公告)日：2016-09-22
申请号：US14659399
申请日：2015-03-16
Applicant: General Electric Company
Inventor： Richard Martin DiCintio , Sarah Lori Crothers
CPC classification number: F02C3/30 , F02C7/228 , F02C9/34 , F05D2270/14 , F05D2270/16 , F23D11/16 , F23K5/12 , F23M20/005 , F23R3/286 , F23R3/343 , F23R2900/00013
Abstract: A system includes a gas turbine engine having a first combustor and a second combustor. Each combustor has at least one fuel nozzle that receives a mixture of liquid fuel and water, via main and pilot fuel supplies, and that injects the mixture and an oxidant into a combustion chamber. A biasing system is disposed in a fuel path upstream of the fuel nozzles in the second combustor to vary the ratios of water/main fuel or water/pilot fuel or the flow rates of such mixtures. The biasing system is configured to help reduce a combustion dynamics amplitude or modal coupling between the first combustor and the second combustor.
Abstract translation: 一种系统包括具有第一燃烧器和第二燃烧器的燃气涡轮发动机。 每个燃烧器具有至少一个燃料喷嘴，其通过主燃料供应和先导燃料供应接收液体燃料和水的混合物，并且将混合物和氧化剂喷射到燃烧室中。 偏置系统设置在第二燃烧器中的燃料喷嘴上游的燃料路径中，以改变水/主燃料或水/引燃燃料的比例或这些混合物的流量。 偏置系统被配置为帮助减少第一燃烧器和第二燃烧器之间的燃烧动力学振幅或模态耦合。
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公开(公告)号：US09291350B2
公开(公告)日：2016-03-22
申请号：US13845407
申请日：2013-03-18
Applicant: General Electric Company
Inventor： Patrick Benedict Melton , Lucas John Stoia , Richard Martin DiCintio
Abstract: A system for supplying a working fluid to a combustor includes a fuel nozzle, a combustion chamber disposed downstream from the fuel nozzle, an inner flow sleeve that circumferentially surrounds the combustion chamber and a plurality of injectors circumferentially arranged around the inner flow sleeve. The plurality of injectors provide for fluid communication through the inner flow sleeve and into the combustion chamber downstream from the fuel nozzle. The system further includes an outer air shield that defines an injection air plenum that surrounds the plurality of injectors. An inlet passage extends through the outer air shield to define a flow path into the injection air plenum. An outer sleeve is slidingly engaged with the outer air shield. The outer sleeve has a first position that restricts flow through the inlet passage and a second position that increases flow through the inlet passage.
Abstract translation: 用于向燃烧器供应工作流体的系统包括燃料喷嘴，设置在燃料喷嘴下游的燃烧室，周向围绕燃烧室的内部流动套筒和围绕内部流动套筒周向布置的多个喷射器。 多个喷射器提供通过内部流动套筒的流体连通并进入燃料喷嘴下游的燃烧室。 该系统还包括限定围绕多个喷射器的喷射空气室的外部空气屏蔽。 入口通道延伸穿过外部空气屏蔽件以限定进入注入空气室的流动路径。 外套筒与外部空气屏蔽滑动接合。 外套筒具有限制通过入口通道的流动的第一位置和增加通过入口通道的流动的第二位置。
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公开(公告)号：US20160017805A1
公开(公告)日：2016-01-21
申请号：US14334219
申请日：2014-07-17
Applicant: General Electric Company
Inventor： Richard Martin DiCintio , Patrick Benedict Melton
Abstract: A combustor cap for a combustor chamber of a combustion system is provided. The combustor cap includes a plate member including: a plurality of openings for accommodating a plurality of fuel nozzles of the combustion system; a cooling passage extending through a plane of the plate member; an entrance opening to the cooling passage; and an exit opening from the cooling passage to a side of the plate member opposite to the combustion chamber.
Abstract translation: 提供了一种用于燃烧系统的燃烧室的燃烧器盖。 燃烧器盖包括板构件，其包括：用于容纳燃烧系统的多个燃料喷嘴的多个开口; 冷却通道，其延伸穿过所述板构件的平面; 通向冷却通道的入口; 以及从冷却通道到板构件与燃烧室相对的一侧的出口。
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50.发明申请COMBUSTOR SUPPORT ASSEMBLY FOR MOUNTING A COMBUSTION MODULE OF A GAS TURBINE 有权用于安装燃气涡轮机燃烧模块的COMBUSTOR支持组件公开(公告)号：US20140260319A1
公开(公告)日：2014-09-18
申请号：US13845699
申请日：2013-03-18
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Patrick Benedict Melton , Lucas John Stoia , Richard Martin DiCintio , Christopher Paul Willis
IPC: F23R3/60
CPC classification number: F23R3/60 , F23R3/005 , F23R3/34 , F23R2900/00017 , F23R2900/00019
Abstract: A gas turbine comprises a compressor discharge casing that is coupled to an outer turbine shell. The compressor discharge casing includes a combustor opening that extends through the compressor discharge casing and an outer mating surface that circumferentially surrounds the combustor opening. The outer turbine shell defines an inner mating surface. A combustion module extends through the combustor opening. The combustion module includes a forward end that is circumferentially surrounded by a mounting flange and an aft end that is circumferentially surrounded by an aft frame. The mounting flange extends circumferentially around the combustor opening. The mounting flange is coupled to the outer mating surface of the compressor discharge casing and the aft frame is coupled to the inner mating surface of the outer turbine shell.
Abstract translation: 燃气轮机包括联接到外部涡轮机壳体的压缩机排出壳体。 压缩机排出壳体包括延伸穿过压缩机排出壳体的燃烧器开口和围绕燃烧器开口的外部配合表面。 外涡轮壳体限定内配合表面。 燃烧模块延伸穿过燃烧器开口。 燃烧模块包括由安装凸缘周向地包围的前端和由后框架周向包围的后端。 安装凸缘围绕燃烧器开口周向延伸。 安装凸缘联接到压缩机排出壳体的外配合表面，并且后框架联接到外涡轮机壳体的内配合表面。
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