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公开(公告)号：US20140013756A1
公开(公告)日：2014-01-16
申请号：US13545272
申请日：2012-07-10
IPC分类号： F02C7/24
CPC分类号： F02C7/22 , F05D2260/96 , F23R3/28 , F23R2900/00014
摘要： A combustor includes an upstream surface that extends radially across at least a portion of the combustor, a downstream surface that extends radially across at least a portion of the combustor and is axially separated from the upstream surface, and a plurality of tubes that extend through the downstream surface. A resonator is upstream from at least one of the tubes, and a fluid passage extends through the resonator and into the least one tube.
摘要翻译： 燃烧器包括径向延伸穿过燃烧器的至少一部分的上游表面，沿着燃烧器的至少一部分径向延伸并且与上游表面轴向分离的下游表面，以及延伸穿过燃烧器的多个管 下游表面。 谐振器位于至少一个管的上游，并且流体通道延伸穿过谐振器并进入至少一个管。
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公开(公告)号：US09249734B2
公开(公告)日：2016-02-02
申请号：US13545272
申请日：2012-07-10
CPC分类号： F02C7/22 , F05D2260/96 , F23R3/28 , F23R2900/00014
摘要： A combustor includes an upstream surface that extends radially across at least a portion of the combustor, a downstream surface that extends radially across at least a portion of the combustor and is axially separated from the upstream surface, and a plurality of tubes that extend through the downstream surface. A resonator is upstream from at least one of the tubes, and a fluid passage extends through the resonator and into the least one tube.
摘要翻译： 燃烧器包括径向延伸穿过燃烧器的至少一部分的上游表面，沿着燃烧器的至少一部分径向延伸并且与上游表面轴向分离的下游表面，以及延伸穿过燃烧器的多个管 下游表面。 谐振器位于至少一个管的上游，并且流体通道延伸穿过谐振器并进入至少一个管。
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公开(公告)号：US08661823B2
公开(公告)日：2014-03-04
申请号：US12652142
申请日：2010-01-05
IPC分类号： F02C1/00
CPC分类号： F02C7/222 , F05B2240/311 , F05D2240/128
摘要： A fuel nozzle for a gas turbine includes a fuel nozzle body or endcover. The fuel nozzle body or endcover includes at least one seal surface. The fuel nozzle also includes at least one flexible hose and at least one flange connected to the flexible hose. The at least one flange is fastened to the fuel nozzle body at the at least one seal surface.
摘要翻译： 用于燃气轮机的燃料喷嘴包括燃料喷嘴体或端盖。 燃料喷嘴体或端盖包括至少一个密封表面。 燃料喷嘴还包括至少一个柔性软管和连接到柔性软管的至少一个凸缘。 所述至少一个凸缘在所述至少一个密封表面处紧固到所述燃料喷嘴体。
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公开(公告)号：US20110162372A1
公开(公告)日：2011-07-07
申请号：US12652142
申请日：2010-01-05
CPC分类号： F02C7/222 , F05B2240/311 , F05D2240/128
摘要： A fuel nozzle for a gas turbine includes a fuel nozzle body or endcover. The fuel nozzle body or endcover includes at least one seal surface. The fuel nozzle also includes at least one flexible hose and at least one flange connected to the flexible hose. The at least one flange is fastened to the fuel nozzle body at the at least one seal surface.
摘要翻译： 用于燃气轮机的燃料喷嘴包括燃料喷嘴体或端盖。 燃料喷嘴体或端盖包括至少一个密封表面。 燃料喷嘴还包括至少一个柔性软管和连接到柔性软管的至少一个凸缘。 所述至少一个凸缘在所述至少一个密封表面处紧固到所述燃料喷嘴体。
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公开(公告)号：US09243507B2
公开(公告)日：2016-01-26
申请号：US13346054
申请日：2012-01-09
摘要： A late lean injection system transition piece includes a flowsleeve interface extending circumferentially around a transition interior. Also included is an impingement sleeve mounting surface extending circumferentially around the transition interior. Further included is a plurality of fuel injectors integrated substantially within the transition piece and disposed between the flowsleeve interface and the impingement sleeve mounting surface. Yet further included is an inner surface extending circumferentially around the transition interior, wherein the inner surface is spaced radially inward of the flowsleeve interface and the impingement sleeve mounting surface.
摘要翻译： 后期的稀薄注射系统过渡件包括围绕过渡内部周向延伸的流动界面。 还包括围绕过渡内部周向延伸的冲击套筒安装表面。 还包括多个基本上集成在过渡件内并且设置在流动接口和冲击套筒安装表面之间的燃料喷射器。 还包括一个围绕过渡内部周向延伸的内表面，其中内表面沿流动界面和冲击套筒安装表面径向向内间隔开。
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公开(公告)号：US08745986B2
公开(公告)日：2014-06-10
申请号：US13545296
申请日：2012-07-10
IPC分类号： F02C3/16
摘要： A fuel supply system for a gas turbine includes a combustion section, a transition duct downstream from the combustion section, a turbine section downstream from the transition duct, and a first stage of stationary vanes circumferentially arranged inside the turbine section. A hot gas path is between the transition duct and the stationary vanes, and a fuel injector provides fluid communication into the hot gas path. A method of supplying fuel to a gas turbine includes combusting a first fuel in a combustion chamber to produce combustion gases, flowing the combustion gases through a transition duct to a hot gas path, and flowing the combustion gases through the hot gas path to a first stage of stationary vanes in a turbine section. The method further includes injecting a second fuel into the hot gas path downstream from the transition duct and upstream from the first stage of stationary vanes.
摘要翻译： 一种用于燃气轮机的燃料供应系统包括燃烧部分，从燃烧部分下游的过渡管道，在过渡管道下游的涡轮部分以及周向布置在涡轮机部分内的静止叶片的第一级。 过渡管道和静止叶片之间的热气体路径，燃料喷射器提供与热气体通道的流体连通。 向燃气轮机供应燃料的方法包括在燃烧室中燃烧第一燃料以产生燃烧气体，使燃烧气体通过过渡管道流动到热气体路径，并使燃烧气体通过热气体路径流动到第一 在涡轮机部分的固定叶片的阶段。 该方法还包括将第二燃料喷射到从过渡管道下游的热气路径和静止叶片的第一级的上游。
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公开(公告)号：US20130318976A1
公开(公告)日：2013-12-05
申请号：US13482584
申请日：2012-05-29
CPC分类号： F23D14/62 , F23R3/283 , F23R3/286 , F23R2900/00018 , Y10T29/49323
摘要： A turbomachine combustor nozzle includes a first plate member having a first plurality of openings, and a second plate member having a second plurality of openings that are configured and disposed to be in alignment with the first plurality of openings. A plurality of nozzle members extends through corresponding ones of the first plurality of openings and the second plurality of openings. Each of the plurality of nozzle members includes a solid core.
摘要翻译： 涡轮机燃烧器喷嘴包括具有第一多个开口的第一板构件和具有第二多个开口的第二板构件，第二多个开口被构造和设置成与第一多个开口对准。 多个喷嘴构件延伸穿过第一多个开口和第二多个开口中的相应的开口。 多个喷嘴构件中的每一个包括实芯。
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公开(公告)号：US20130180253A1
公开(公告)日：2013-07-18
申请号：US13349886
申请日：2012-01-13
IPC分类号： F23R3/28
摘要： A system for supplying a working fluid to a combustor includes a fuel nozzle, a combustion chamber, and fuel injectors circumferentially arranged around the combustion chamber. A combustor casing surrounds the combustion chamber. A distribution manifold encloses the fuel injectors, and a plenum passes through the combustor casing. A method for supplying a working fluid to a combustor includes flowing a working fluid from a compressor through a combustion chamber, diverting a portion of the working fluid into a plenum, and flowing the diverted portion of the working fluid outside of the compressor and the combustor. The method further includes flowing the diverted portion of the working fluid through a combustor casing and through a distribution manifold that encloses fuel injectors circumferentially arranged around the combustion chamber.
摘要翻译： 用于向燃烧器供应工作流体的系统包括燃料喷嘴，燃烧室和围绕燃烧室周向布置的燃料喷射器。 燃烧器壳体围绕燃烧室。 分配歧管围绕燃料喷射器，并且气室通过燃烧器壳体。 将工作流体供给到燃烧器的方法包括使来自压缩机的工作流体流过燃烧室，将工作流体的一部分转移到集气室中，并使工作流体的转向部分流出压缩机和燃烧器外部 。 该方法还包括使工作流体的转向部分流过燃烧器壳体并且通过围绕燃烧室周向布置的围绕燃料喷射器的分配歧管流动。
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公开(公告)号：US20130174561A1
公开(公告)日：2013-07-11
申请号：US13346054
申请日：2012-01-09
摘要： A late lean injection system transition piece includes a flowsleeve interface extending circumferentially around a transition interior. Also included is an impingement sleeve mounting surface extending circumferentially around the transition interior. Further included is a plurality of fuel injectors integrated substantially within the transition piece and disposed between the flowsleeve interface and the impingement sleeve mounting surface. Yet further included is an inner surface extending circumferentially around the transition interior, wherein the inner surface is spaced radially inward of the flowsleeve interface and the impingement sleeve mounting surface.
摘要翻译： 后期的稀薄注射系统过渡件包括围绕过渡内部周向延伸的流动界面。 还包括围绕过渡内部周向延伸的冲击套筒安装表面。 还包括多个基本上集成在过渡件内并且设置在流动接口和冲击套筒安装表面之间的燃料喷射器。 还包括一个围绕过渡内部周向延伸的内表面，其中内表面沿流动界面和冲击套筒安装表面径向向内间隔开。
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公开(公告)号：US20130167542A1
公开(公告)日：2013-07-04
申请号：US13343200
申请日：2012-01-04
IPC分类号： F02C7/22
摘要： A flowsleeve of a turbomachine component is provided. The flowsleeve includes an annular body including an upstream casing and a downstream casing. The upstream casing defines a fuel feed, and the downstream casing defines an airway opening, and a premixing passage. The premixing passage is fluidly coupled to the fuel feed and the airway opening and has a passage interior in which fuel and air receivable from the fuel feed and the airway opening, respectively, are combinable to form a fuel and air mixture.
摘要翻译： 提供涡轮机组件的流动。 流水线包括包括上游壳体和下游壳体的环形体。 上游壳体限定燃料供给，并且下游壳体限定气道开口和预混合通道。 预混合通道流体地联接到燃料进料和气道开口并且具有通道内部，分别从燃料进料和气道开口接收的燃料和空气可组合以形成燃料和空气混合物。
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