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公开(公告)号：US20150253011A1
公开(公告)日：2015-09-10
申请号：US14719356
申请日：2015-05-22
Applicant: General Electric Company
Inventor： Jong Ho Uhm , Derrick Walter Simons , Gregory Allen Boardman , Bryan Wesley Romig , Kara Edwards , Michael John Hughes
CPC classification number: F23R3/286 , F23C7/004 , F23C2900/07001 , F23D14/08 , F23R3/14 , F23R3/343 , F23R2900/03343
Abstract: A combustor for a gas turbine engine has a head end portion that carries at least one fuel/air nozzle. Each fuel/air nozzle includes a premixed pilot nozzle having premix conduits where each premix conduit has an upstream end defining an opening and having a central axis and downstream end defining an outlet and having a central axis where the central axis of the downstream end is non-parallel with a central axis of a center body of the fuel/air nozzle. The premixed pilot nozzle can include an annular channel disposed radially outwardly from the premix conduits and may include air jets that direct air radially outwardly from the premix conduits.
Abstract translation: 用于燃气涡轮发动机的燃烧器具有承载至少一个燃料/空气喷嘴的头端部分。 每个燃料/空气喷嘴包括具有预混合管道的预混合先导喷嘴，其中每个预混管道具有限定开口的上游端，并且具有中心轴线和下游端限定出口，并且具有中心轴线，其中下游端的中心轴线不是 与燃料/空气喷嘴的中心体的中心轴平行。 预混合引导喷嘴可以包括从预混合管道径向向外设置的环形通道，并且可以包括从预混管道径向向外引导空气的空气射流。
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2.发明申请Combustion Casing Manifold for High Pressure Air Delivery to a Fuel Nozzle Pilot System 有权用于高压空气输送到燃油喷嘴试验系统的燃烧套管歧管公开(公告)号：US20150128606A1
公开(公告)日：2015-05-14
申请号：US14076360
申请日：2013-11-11
Applicant: General Electric Company
Inventor： Bryan Wesley Romig , Brandon Taylor Overby
IPC: F23R3/28
Abstract: The present application provides a pilot manifold system for a combustor of a gas turbine engine. The pilot manifold system may include a casing with a casing manifold, an end cover connected to the casing and having an end cover passage in communication with the casing manifold, and a fuel nozzle mounted about the end cover. The fuel nozzle may include a pilot system in communication with the end cover passage.
Abstract translation: 本申请提供了一种用于燃气涡轮发动机的燃烧器的先导歧管系统。 先导歧管系统可以包括具有套管歧管的壳体，连接到壳体的端盖并且具有与套管歧管连通的端盖通道以及围绕端盖安装的燃料喷嘴。 燃料喷嘴可以包括与端盖通道连通的先导系统。
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公开(公告)号：US20140116066A1
公开(公告)日：2014-05-01
申请号：US13663712
申请日：2012-10-30
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Patrick Benedict Melton , Bryan Wesley Romig , Lucas John Stoia
CPC classification number: F23R3/286 , F23D11/36 , F23D14/78 , F23D2214/00 , F23R3/14 , F23R3/28 , F23R3/283 , F23R2900/03043 , F23R2900/03044
Abstract: A combustor generally includes a shroud that that defines at least one inlet passage extends circumferentially inside the combustor. A first plate extends radially inside the shroud downstream from the inlet passage. The first plate defines at least one inlet port, at least one outlet port and at least partially defines at least one fuel nozzle passage. The shroud at least partially surrounds a sleeve that extends around the fuel nozzle passage. A tube at least partially surrounded by the sleeve may extend through the fuel nozzle passage. The tube, the sleeve, and the first plate may at least partially define an outlet passage. A first fluid flow path generally extends from the at inlet passage to the inlet port, and a second fluid flow path extends generally from the outlet port to the outlet passage.
Abstract translation: 燃烧器通常包括护罩，其限定在燃烧器内周向延伸的至少一个入口通道。 第一板在入口通道下游的护罩的径向内部延伸。 第一板限定至少一个入口端口，至少一个出口端口，并且至少部分地限定至少一个燃料喷嘴通道。 护罩至少部分地围绕围绕燃料喷嘴通道延伸的套筒。 至少部分地被套筒包围的管可延伸穿过燃料喷嘴通道。 管，套筒和第一板可以至少部分地限定出口通道。 第一流体流动路径通常从入口通道延伸到入口端口，并且第二流体流动路径大体上从出口延伸到出口通道。
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公开(公告)号：US09982892B2
公开(公告)日：2018-05-29
申请号：US14688170
申请日：2015-04-16
Applicant: General Electric Company
Inventor： Bryan Wesley Romig , Dereck Joseph Ouellet , Jason Thurman Stewart , Michael Christopher Gibson
CPC classification number: F23R3/343 , F23R3/14 , F23R3/286 , F23R2900/03343
Abstract: A fuel nozzle assembly includes a center body having a pilot air passage and a pilot fuel passage defined therein. A pilot nozzle having a plurality of premix passages is disposed within a downstream end portion of the center body. Each premix passage includes an inlet that is in fluid communication with the pilot air passage, an outlet that is positioned axially downstream from the inlet and a fuel port that is in fluid communication with the pilot fuel passage. An outer sleeve is coaxially aligned with and radially spaced from the center body so as to define an annular passage therebetween. A strut extends radially outwardly from the center body to the outer sleeve. The fuel nozzle assembly further includes an inlet passage that is in fluid communication with the pilot air passage. The inlet passage extends through the outer sleeve, the strut and the center body.
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公开(公告)号：US20160305668A1
公开(公告)日：2016-10-20
申请号：US14688170
申请日：2015-04-16
Applicant: General Electric Company
Inventor： Bryan Wesley Romig , Dereck Joseph Ouellet , Jason Thurman Stewart , Michael Christopher Gibson
CPC classification number: F23R3/343 , F23R3/14 , F23R3/286 , F23R2900/03343
Abstract: A fuel nozzle assembly includes a center body having a pilot air passage and a pilot fuel passage defined therein. A pilot nozzle having a plurality of premix passages is disposed within a downstream end portion of the center body. Each premix passage includes an inlet that is in fluid communication with the pilot air passage, an outlet that is positioned axially downstream from the inlet and a fuel port that is in fluid communication with the pilot fuel passage. An outer sleeve is coaxially aligned with and radially spaced from the center body so as to define an annular passage therebetween. A strut extends radially outwardly from the center body to the outer sleeve. The fuel nozzle assembly further includes an inlet passage that is in fluid communication with the pilot air passage. The inlet passage extends through the outer sleeve, the strut and the center body.
Abstract translation: 燃料喷嘴组件包括具有先导空气通道和限定在其中的先导燃料通道的中心体。 具有多个预混通道的先导喷嘴设置在中心体的下游端部内。 每个预混通道包括与导向空气通道流体连通的入口，位于轴向入口下游的出口和与引燃燃料通道流体连通的燃料口。 外套筒与中心体同轴对准并且与其径向间隔开，从而在它们之间形成环形通道。 支柱从中心体径向向外延伸到外套筒。 燃料喷嘴组件还包括与先导空气通道流体连通的入口通道。 入口通道延伸穿过外套筒，支柱和中心体。
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Patent Agency Ranking
公开(公告)号：US20160177837A1
公开(公告)日：2016-06-23
申请号：US15058418
申请日：2016-03-02
Applicant: General Electric Company
Inventor： Jong Ho Uhm , Bryan Wesley Romig , Yon Han Chong
CPC classification number: F02C7/222 , F02C3/04 , F05D2220/32 , F05D2240/127 , F23C2900/07001 , F23D2900/14021 , F23R3/14 , F23R3/286
Abstract: A fuel nozzle includes an inner wall defining a central passage extending in an axial direction of the fuel nozzle, a hub wall surrounding the inner wall and defining a first annular passage, an outer wall surrounding the hub wall and defining a second annular passage, and a shroud surrounding the outer wall and defining a third annular passage. A swirler may receive air and direct the air into the first annular passage. The swirler includes at least one swirl vane extending from the shroud to the hub wall that has an air passage extending between the shroud and the hub wall. The air passage is coupled to the first annular passage and has a first width adjacent the shroud and a second width adjacent the hub wall. The second width is larger than the first width defining a diverging outlet into the first annular passage.
Abstract translation: 燃料喷嘴包括限定沿着燃料喷嘴的轴向方向延伸的中心通道的内壁，围绕内壁并限定第一环形通道的毂壁，围绕毂壁并限定第二环形通道的外壁，以及 围绕外壁并限定第三环形通道的护罩。 旋流器可以接收空气并将空气引导到第一环形通道中。 旋流器包括从护罩延伸到毂壁的至少一个旋流叶片，其具有在护罩和轮毂壁之间延伸的空气通道。 空气通道联接到第一环形通道并且具有与护罩相邻的第一宽度和邻近轮毂壁的第二宽度。 第二宽度大于限定到第一环形通道的发散出口的第一宽度。
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7.发明申请SYSTEM AND METHOD 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：US20150330636A1
公开(公告)日：2015-11-19
申请号：US14276700
申请日：2014-05-13
Applicant: General Electric Company
Inventor： Sarah Lori Crothers , Charlotte Cole Wilson , Bryan Wesley Romig
CPC classification number: F02C7/228 , F02C9/263 , F23R3/28 , F23R3/34 , F23R2900/00014 , Y02T50/672
Abstract: A system includes a gas turbine engine that includes a first combustor and a second combustor. The first combustor includes a first fuel nozzle disposed in a first head end chamber of the first combustor. The first fuel nozzle includes a first orifice configured to inject fuel into a first combustion chamber of the first combustor. The second combustor includes a second fuel nozzle disposed in a second head end chamber of the second combustor. The second fuel nozzle includes a second orifice configured to inject the fuel into a second combustion chamber of the second combustor. The second combustor also includes a second orifice plate disposed in a fuel path upstream of the second orifice. The second orifice plate is configured to help reduce modal coupling between the first combustor and the second combustor.
Abstract translation: 一种系统包括包括第一燃烧器和第二燃烧器的燃气涡轮发动机。 第一燃烧器包括设置在第一燃烧器的第一头端室中的第一燃料喷嘴。 第一燃料喷嘴包括构造成将燃料喷射到第一燃烧器的第一燃烧室中的第一孔。 第二燃烧器包括设置在第二燃烧器的第二头端室中的第二燃料喷嘴。 第二燃料喷嘴包括构造成将燃料喷射到第二燃烧器的第二燃烧室中的第二孔口。 第二燃烧器还包括设置在第二孔口上游的燃料路径中的第二孔板。 第二孔板构造成有助于减小第一燃烧器和第二燃烧器之间的模态耦合。
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公开(公告)号：US20140202160A1
公开(公告)日：2014-07-24
申请号：US13749661
申请日：2013-01-24
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Bryan Wesley Romig , Brandon Taylor Overby
IPC: F02C7/00
CPC classification number: F02C7/00 , F02C7/222 , F23R3/045 , F23R3/10 , F23R3/46 , F23R3/60 , F23R2900/00017 , Y02T50/675
Abstract: A system including a gas turbine engine, including a combustor configured to generate products of combustion, a turbine driven by the products of combustion from the combustor, a compressor having a compressor discharge leading into a chamber between the combustor and a compressor discharge casing, an extraction manifold coupled to the combustor, wherein the extraction manifold is fluidly coupled to the chamber.
Abstract translation: 一种包括燃气涡轮发动机的系统，包括构造成产生燃烧产物的燃烧器，由来自燃烧器的燃烧产物驱动的涡轮机，具有通向燃烧器和压缩机排出壳体之间的室中的压缩机排出口的压缩机， 抽吸歧管联接到燃烧器，其中提取歧管流体耦合到腔室。
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公开(公告)号：US10415479B2
公开(公告)日：2019-09-17
申请号：US15058418
申请日：2016-03-02
Applicant: General Electric Company
Inventor： Jong Ho Uhm , Bryan Wesley Romig , Yon Han Chong
Abstract: A fuel nozzle includes an inner wall defining a central passage extending in an axial direction of the fuel nozzle, a hub wall surrounding the inner wall and defining a first annular passage, an outer wall surrounding the hub wall and defining a second annular passage, and a shroud surrounding the outer wall and defining a third annular passage. A swirler may receive air and direct the air into the first annular passage. The swirler includes at least one swirl vane extending from the shroud to the hub wall that has an air passage extending between the shroud and the hub wall. The air passage is coupled to the first annular passage and has a first width adjacent the shroud and a second width adjacent the hub wall. The second width is larger than the first width defining a diverging outlet into the first annular passage.
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公开(公告)号：US09869279B2
公开(公告)日：2018-01-16
申请号：US14067559
申请日：2013-10-30
Inventor： Lucas John Stoia , Richard Martin DiCintio , Patrick Benedict Melton , Bryan Wesley Romig , Ilya Aleksandrovich Slobodyanskiy
IPC: F02C3/00 , F02C9/00 , F23R3/46 , F02M25/07 , F02C3/34 , F23C9/00 , F23R3/00 , F23R3/06 , F02M26/19 , F02C3/13
CPC classification number: F02M26/19 , F02C3/13 , F02C3/34 , F23C9/00 , F23R3/005 , F23R3/06 , F23R3/46 , F23R2900/03044 , F23R2900/03045 , Y02E20/16 , Y02T50/675
Abstract: A system includes a turbine combustor, which includes a first wall disposed about a combustion chamber, a second wall disposed about the first wall, and a third wall disposed about the second wall. The third wall is configured to combine an exhaust gas with an oxidant and the combustion chamber is configured to combust a mixture of a fuel, the oxidant, and the exhaust gas.
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