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公开(公告)号：US20120304657A1
公开(公告)日：2012-12-06
申请号：US13153987
申请日：2011-06-06
申请人： Patrick Benedict MELTON , Keith Cletus Belsom , Thomas Edward Johnson , William Lawrence Byrne , Robert Joseph Rohrssen
发明人： Patrick Benedict MELTON , Keith Cletus Belsom , Thomas Edward Johnson , William Lawrence Byrne , Robert Joseph Rohrssen
CPC分类号： F23R3/60 , F23R2900/00012
摘要： A flexible annular seal for insertion between concentrically assembled turbine combustor components includes an annular inner seal portion having a first solid annular edge and first plurality of spring fingers extending axially from the first solid annular edge; and an annular outer seal portion having a second solid annular edge and a second plurality of spring fingers extending axially from the second solid edge and overlying the first plurality of spring fingers such that the inner and outer seal portions are substantially fully engaged along an entire length dimension of the flexible annular seal. The second plurality of spring fingers are circumferentially offset from the first plurality of spring fingers, and free ends of the first plurality of spring fingers are bent around and over free ends of the second plurality of spring fingers.
摘要翻译： 用于插入在同心组装的涡轮机燃烧器部件之间的柔性环形密封件包括环形内密封部分，其具有第一固体环形边缘和从第一固体环形边缘轴向延伸的第一多个弹簧指状件; 以及环形外密封部分，其具有第二固体环形边缘和从第二实心边缘轴向延伸并且覆盖第一多个弹簧指的第二多个弹簧指，使得内部和外部密封部分沿着整个长度基本上完全接合 柔性环形密封件的尺寸。 第二多个弹簧指沿周向偏离第一多个弹簧指，并且第一多个弹簧指的自由端围绕第二多个弹簧指的自由端弯曲并弯曲。
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公开(公告)号：US20140020389A1
公开(公告)日：2014-01-23
申请号：US13555481
申请日：2012-07-23
IPC分类号： F23R3/46
CPC分类号： F23R3/10 , F23R3/283 , F23R3/46 , F23R2900/03042 , F23R2900/03044
摘要： One embodiment of the present invention is a cap insert for a combustor fuel nozzle cap assembly. The cap insert generally includes a cap plate that defines a fuel nozzle passage and may have an upstream peripheral edge. An impingement plate having a body may generally define an axially extending annular sleeve and a radially outer portion that circumferentially surrounds the body. The radially outer portion may include an upstream end axially separated from a downstream end. The axially extending annular sleeve may define an annular passage through the body. The cap plate upstream peripheral edge may be contiguous with the downstream end of the impingement plate body radially outer portion.
摘要翻译： 本发明的一个实施例是用于燃烧器燃料喷嘴盖组件的盖插件。 盖插件通常包括限定燃料喷嘴通道并且可具有上游周边边缘的盖板。 具有主体的冲击板可以大致限定轴向延伸的环形套筒和周向围绕主体的径向外部部分。 径向外部可包括与下游端轴向分离的上游端。 轴向延伸的环形套筒可以限定通过本体的环形通道。 盖板上游周边边缘可以与冲击板主体径向外部的下游端相邻。
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公开(公告)号：US09175857B2
公开(公告)日：2015-11-03
申请号：US13555481
申请日：2012-07-23
CPC分类号： F23R3/10 , F23R3/283 , F23R3/46 , F23R2900/03042 , F23R2900/03044
摘要： One embodiment of the present invention is a cap insert for a combustor fuel nozzle cap assembly. The cap insert generally includes a cap plate that defines a fuel nozzle passage and may have an upstream peripheral edge. An impingement plate having a body may generally define an axially extending annular sleeve and a radially outer portion that circumferentially surrounds the body. The radially outer portion may include an upstream end axially separated from a downstream end. The axially extending annular sleeve may define an annular passage through the body. The cap plate upstream peripheral edge may be contiguous with the downstream end of the impingement plate body radially outer portion.
摘要翻译： 本发明的一个实施例是用于燃烧器燃料喷嘴盖组件的盖插件。 盖插件通常包括限定燃料喷嘴通道并且可具有上游周边边缘的盖板。 具有主体的冲击板可以大致限定轴向延伸的环形套筒和周向围绕主体的径向外部部分。 径向外部可包括与下游端轴向分离的上游端。 轴向延伸的环形套筒可以限定通过本体的环形通道。 盖板上游周边边缘可以与冲击板主体径向外部的下游端相邻。
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4.发明授权Turbomachine combustor nozzle including a monolithic nozzle component and method of forming the same 有权涡轮机燃烧器喷嘴包括单片喷嘴部件及其形成方法公开(公告)号：US09267690B2
公开(公告)日：2016-02-23
申请号：US13482540
申请日：2012-05-29
申请人： Lucas John Stoia , Patrick Benedict Melton , Thomas Edward Johnson , Christian Xavier Stevenson , John Drake Vanselow , James Harold Westmoreland
发明人： Lucas John Stoia , Patrick Benedict Melton , Thomas Edward Johnson , Christian Xavier Stevenson , John Drake Vanselow , James Harold Westmoreland
CPC分类号： F23R3/283 , F23R3/286 , F23R2900/00017 , F23R2900/00018 , Y10T29/49323
摘要： A turbomachine combustor nozzle includes a monolithic nozzle component having a plate element and a plurality of nozzle elements. Each of the plurality of nozzle elements includes a first end extending from the plate element to a second end. The plate element and plurality of nozzle elements are formed as a unitary component. A plate member is joined with the nozzle component. The plate member includes an outer edge that defines first and second surfaces and a plurality of openings extending between the first and second surfaces. The plurality of openings are configured and disposed to register with and receive the second end of corresponding ones of the plurality of nozzle elements.
摘要翻译： 涡轮机燃烧器喷嘴包括具有板元件和多个喷嘴元件的单片喷嘴部件。 多个喷嘴元件中的每一个包括从板元件延伸到第二端的第一端。 板元件和多个喷嘴元件形成为整体部件。 板构件与喷嘴部件接合。 板构件包括限定第一和第二表面的外边缘和在第一和第二表面之间延伸的多个开口。 多个开口被配置和设置成与多个喷嘴元件中对应的喷嘴元件的对应的第二端对准并接收。
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5.发明授权公开(公告)号：US09200808B2
公开(公告)日：2015-12-01
申请号：US13457726
申请日：2012-04-27
申请人： Bryan Wesley Romig , Lucas John Stoia , Patrick Benedict Melton , Thomas Edward Johnson , Gregory Allen Boardman
发明人： Bryan Wesley Romig , Lucas John Stoia , Patrick Benedict Melton , Thomas Edward Johnson , Gregory Allen Boardman
摘要： A system for supplying fuel to a combustor includes a combustion chamber and a fuel nozzle that provides fluid communication into the combustion chamber. A plurality of passages circumferentially arranged around the combustion chamber provide fluid communication into the combustion chamber. A liquid fuel plenum provides fluid communication to the plurality of passages. A baffle circumferentially surrounds at least a portion of the liquid fuel plenum inside the plurality of passages and forms a plurality of lobes around the liquid fuel plenum.
摘要翻译： 用于向燃烧器供应燃料的系统包括提供与燃烧室的流体连通的燃烧室和燃料喷嘴。 围绕燃烧室周向布置的多个通道提供流体连通到燃烧室中。 液体燃料增压室提供与多个通道的流体连通。 挡板周向地围绕多个通道内的液体燃料增压室的至少一部分，并在液体燃料增压室周围形成多个叶片。
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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：US08079219B2
公开(公告)日：2011-12-20
申请号：US12242013
申请日：2008-09-30
IPC分类号： F02C1/00
CPC分类号： F23R3/44 , F23R2900/00012 , F23R2900/03044 , Y02T50/675
摘要： Disclosed is a combustor seal including a seal support locatable at a first combustor component and having a plurality of through impingement holes. A wave-shaped seal located at the seal support and defining at least one seal cavity between the wave-shaped seal and the seal support. A peak of the wave-shaped seal is locatable at a second combustor component. The wave-shaped seal includes at least one through passageway located upstream of the peak capable of flowing cooling fluid therethrough into the at least one seal cavity and through the plurality of impingement holes thereby cooling the first combustor component. Further disclosed is a combustor including a combustor seal and a method for cooling a first combustor component.
摘要翻译： 公开了一种燃烧器密封件，其包括可定位在第一燃烧器部件处并具有多个通过冲击孔的密封支撑件。 位于密封支撑件处的波形密封件并且在波形密封件和密封件支撑件之间限定至少一个密封腔。 波形密封件的峰值位于第二燃烧器部件处。 波形密封件包括位于峰顶部的至少一个贯通通道，其能够将冷却流体从其中流动通过其中进入至少一个密封空腔中，并且穿过多个冲击孔从而冷却第一燃烧器部件。 还公开了一种包括燃烧器密封件和用于冷却第一燃烧器部件的方法的燃烧器。
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公开(公告)号：US20100077761A1
公开(公告)日：2010-04-01
申请号：US12242013
申请日：2008-09-30
CPC分类号： F23R3/44 , F23R2900/00012 , F23R2900/03044 , Y02T50/675
摘要： Disclosed is a combustor seal including a seal support locatable at a first combustor component and having a plurality of through impingement holes. A wave-shaped seal located at the seal support and defining at least one seal cavity between the wave-shaped seal and the seal support. A peak of the wave-shaped seal is locatable at a second combustor component. The wave-shaped seal includes at least one through passageway located upstream of the peak capable of flowing cooling fluid therethrough into the at least one seal cavity and through the plurality of impingement holes thereby cooling the first combustor component. Further disclosed is a combustor including a combustor seal and a method for cooling a first combustor component.
摘要翻译： 公开了一种燃烧器密封件，其包括可定位在第一燃烧器部件处并具有多个通过冲击孔的密封支撑件。 位于密封支撑件处的波形密封件并且在波形密封件和密封件支撑件之间限定至少一个密封腔。 波形密封件的峰值位于第二燃烧器部件处。 波形密封件包括位于峰顶部的至少一个贯通通道，其能够将冷却流体从其中流动通过其中进入至少一个密封空腔中，并且穿过多个冲击孔从而冷却第一燃烧器部件。 还公开了一种包括燃烧器密封件和用于冷却第一燃烧器部件的方法的燃烧器。
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公开(公告)号：US20140013723A1
公开(公告)日：2014-01-16
申请号：US13545296
申请日：2012-07-10
IPC分类号： F02C3/30
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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10.发明申请TURBOMACHINE COMBUSTOR NOZZLE INCLUDING A MONOLITHIC NOZZLE COMPONENT AND METHOD OF FORMING THE SAME 有权涡轮喷雾器喷嘴，包括单声道喷嘴组件及其形成方法公开(公告)号：US20130318975A1
公开(公告)日：2013-12-05
申请号：US13482540
申请日：2012-05-29
申请人： Lucas John Stoia , Patrick Benedict Melton , Thomas Edward Johnson , Christian Xavier Stevenson , John Drake Vanselow , James Harold Westmoreland
发明人： Lucas John Stoia , Patrick Benedict Melton , Thomas Edward Johnson , Christian Xavier Stevenson , John Drake Vanselow , James Harold Westmoreland
CPC分类号： F23R3/283 , F23R3/286 , F23R2900/00017 , F23R2900/00018 , Y10T29/49323
摘要： A turbomachine combustor nozzle includes a monolithic nozzle component having a plate element and a plurality of nozzle elements. Each of the plurality of nozzle elements includes a first end extending from the plate element to a second end. The plate element and plurality of nozzle elements are formed as a unitary component. A plate member is joined with the nozzle component. The plate member includes an outer edge that defines first and second surfaces and a plurality of openings extending between the first and second surfaces. The plurality of openings are configured and disposed to register with and receive the second end of corresponding ones of the plurality of nozzle elements.
摘要翻译： 涡轮机燃烧器喷嘴包括具有板元件和多个喷嘴元件的单片喷嘴部件。 多个喷嘴元件中的每一个包括从板元件延伸到第二端的第一端。 板元件和多个喷嘴元件形成为整体部件。 板构件与喷嘴部件接合。 板构件包括限定第一和第二表面的外边缘和在第一和第二表面之间延伸的多个开口。 多个开口被配置和设置成与多个喷嘴元件中对应的喷嘴元件的对应的第二端对准并接收。
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