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公开(公告)号：US20130283806A1
公开(公告)日：2013-10-31
申请号：US13456602
申请日：2012-04-26
申请人： James Christopher Monaghan , Thomas Edward Johnson , Johnie F. McConnaughhay , Heath Michael Ostebee
发明人： James Christopher Monaghan , Thomas Edward Johnson , Johnie F. McConnaughhay , Heath Michael Ostebee
CPC分类号： F23R3/045 , F23R3/06 , F23R2900/00017 , F23R2900/00019 , Y10T29/49346
摘要： A combustor generally includes a liner that at least partially defines a combustion chamber within the combustor. The liner may generally include a hole that extends through the liner and that at least partially defines a mating surface. An insert having an outer surface extends at least partially through the hole. A projection that at least partially defines a mating surface at least partially circumferentially surrounds the insert outer surface. A joint between the projection mating surface and the hole mating surface provides a connection point between the projection mating surface and the liner hole mating surface.
摘要翻译： 燃烧器通常包括至少部分地限定燃烧器内的燃烧室的衬套。 衬里通常可以包括延伸穿过衬套并且至少部分地限定配合表面的孔。 具有外表面的插入件至少部分延伸穿过孔。 至少部分地限定配合表面的突起至少部分地圆周地包围插入物外表面。 突起配合表面和孔匹配表面之间的接头提供了突出配合表面和衬套孔配合表面之间的连接点。
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公开(公告)号：US09506654B2
公开(公告)日：2016-11-29
申请号：US13213460
申请日：2011-08-19
申请人： Jong Ho Uhm , Willy Steve Ziminsky , Thomas Edward Johnson , Shiva Srinivasan , William David York
发明人： Jong Ho Uhm , Willy Steve Ziminsky , Thomas Edward Johnson , Shiva Srinivasan , William David York
摘要： A system for reducing combustion dynamics in a combustor includes an end cap that extends radially across the combustor and includes an upstream surface axially separated from a downstream surface. A combustion chamber is downstream of the end cap, and tubes extend from the upstream surface through the downstream surface. Each tube provides fluid communication through the end cap to the combustion chamber. The system further includes means for reducing combustion dynamics in the combustor. A method for reducing combustion dynamics in a combustor includes flowing a working fluid through tubes that extend axially through an end cap that extends radially across the combustor and obstructing at least a portion of the working fluid flowing through a first set of the tubes.
摘要翻译： 用于减少燃烧器中的燃烧动力学的系统包括：端盖，其径向延伸穿过燃烧器并且包括与下游表面轴向分离的上游表面。 燃烧室在端盖的下游，并且管从上游表面延伸穿过下游表面。 每个管提供通过端盖到燃烧室的流体连通。 该系统还包括用于减少燃烧器中的燃烧动力学的装置。 用于减少燃烧器中的燃烧动力学的方法包括使工作流体通过管轴流动，所述管道轴向延伸穿过径向延伸穿过燃烧器的端盖，并阻塞流过第一组管的至少一部分工作流体。
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3.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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公开(公告)号：US09121612B2
公开(公告)日：2015-09-01
申请号：US13409309
申请日：2012-03-01
CPC分类号： F23R3/286 , F02C3/30 , F23C2900/07022 , F23D14/62 , F23R3/002 , F23R3/32 , F23R3/54 , F23R2900/00013
摘要： A system for reducing combustion dynamics in a combustor includes an end cap having an upstream surface axially separated from a downstream surface, and tube bundles extend from the upstream surface through the downstream surface. A divider inside a tube bundle defines a diluent passage that extends axially through the downstream surface, and a diluent supply in fluid communication with the divider provides diluent flow to the diluent passage. A method for reducing combustion dynamics in a combustor includes flowing a fuel through tube bundles, flowing a diluent through a diluent passage inside a tube bundle, wherein the diluent passage extends axially through at least a portion of the end cap into a combustion chamber, and forming a diluent barrier in the combustion chamber between the tube bundle and at least one other adjacent tube bundle.
摘要翻译： 用于减少燃烧器中的燃烧动力学的系统包括具有从下游表面轴向分离的上游表面的端盖，并且管束从上游表面延伸穿过下游表面。 管束内的分隔器限定了一个沿轴向延伸穿过下游表面的稀释剂通道，与分隔器流体连通的稀释剂供应器提供稀释剂流向稀释剂通道。 一种用于减少燃烧动力学的方法，包括使燃料通过管束流动，使稀释剂流过管束内的稀释剂通道，其中稀释剂通道轴向延伸通过端盖的至少一部分进入燃烧室，以及 在管束与至少一个其它相邻管束之间的燃烧室中形成稀释剂阻挡层。
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公开(公告)号：US08794545B2
公开(公告)日：2014-08-05
申请号：US12567022
申请日：2009-09-25
IPC分类号： F23D11/10
CPC分类号： F23D14/02 , F23C2900/9901 , F23D14/78 , F23D2214/00 , F23R3/286
摘要： A fuel injector includes a fuel delivery tube; a plurality of pre-mixing tubes, each pre-mixing tube comprising at least one fuel injection hole; an upstream tube support plate that supports upstream ends of the plurality of pre-mixing tubes; a downstream tube support plate that supports downstream ends of the plurality of pre-mixing tubes; an outer wall connecting the upstream tube support plate and the downstream tube support plate and defining a plenum therewith; and a baffle provided in the plenum. The baffle includes a radial portion. A fuel delivered in the upstream direction by the fuel delivery tube is directed radially outwardly in the plenum between the radial portion of the baffle and the downstream tube support plate, then in the downstream direction around an outer edge portion of the radial portion, and then radially inwardly between the radial portion and the upstream tube support plate.
摘要翻译： 燃料喷射器包括燃料输送管; 多个预混合管，每个预混合管包括至少一个燃料喷射孔; 上游管支撑板，其支撑所述多个预混合管的上游端; 下游管支撑板，其支撑所述多个预混合管的下游端; 连接所述上游管支撑板和所述下游管支撑板并且与所述下游管支撑板连接的外壁; 以及设置在气室中的挡板。 挡板包括径向部分。 通过燃料输送管沿上游方向输送的燃料径向向外指向在挡板的径向部分和下游管支撑板之间的增压室中，然后在径向部分的外边缘部分的下游方向上，然后 在径向部分和上游管支撑板之间径向向内。
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公开(公告)号：US08733108B2
公开(公告)日：2014-05-27
申请号：US12833237
申请日：2010-07-09
CPC分类号： F23R3/28 , F23C5/08 , F23R2900/00014
摘要： The present application provides for a combustor for use with a gas turbine engine. The combustor may include a cap member and a number of fuel nozzles extending through the cap member. One or more of the fuel nozzles may be provided in a non-flush position with respect to the cap member.
摘要翻译： 本申请提供了一种与燃气涡轮发动机一起使用的燃烧器。 燃烧器可以包括盖构件和延伸穿过帽构件的多个燃料喷嘴。 一个或多个燃料喷嘴可以相对于盖构件设置在非冲洗位置。
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7.发明授权Turbine combustor with fuel nozzles having inner and outer fuel circuits 有权具有燃料喷嘴的涡轮机燃烧器具有内部和外部燃料回路公开(公告)号：US08613197B2
公开(公告)日：2013-12-24
申请号：US12850763
申请日：2010-08-05
申请人： Jong Ho Uhm , Thomas Edward Johnson , Kwanwoo Kim
发明人： Jong Ho Uhm , Thomas Edward Johnson , Kwanwoo Kim
CPC分类号： F23R3/34 , F02C7/222 , F05D2260/96 , F23N1/002 , F23N2037/02 , F23R3/28 , F23R3/46 , F23R2900/00013
摘要： A combustor cap assembly for a turbine engine includes a combustor cap and a plurality of fuel nozzles mounted on the combustor cap. One or more of the fuel nozzles would include two separate fuel circuits which are individually controllable. The combustor cap assembly would be controlled so that individual fuel circuits of the fuel nozzles are operated or deliberately shut off to provide for physical separation between the flow of fuel delivered by adjacent fuel nozzles and/or so that adjacent fuel nozzles operate at different pressure differentials. Operating a combustor cap assembly in this fashion helps to reduce or eliminate the generation of undesirable and potentially harmful noise.
摘要翻译： 用于涡轮发动机的燃烧器盖组件包括燃烧器盖和安装在燃烧器盖上的多个燃料喷嘴。 一个或多个燃料喷嘴将包括可独立控制的两个单独的燃料回路。 将控制燃烧器盖组件，使得燃料喷嘴的各个燃料回路被操作或故意切断以提供由相邻燃料喷嘴输送的燃料流之间的物理分离和/或使得相邻燃料喷嘴在不同的压差下工作 。 以这种方式操作燃烧器盖组件有助于减少或消除不期望的和潜在的有害噪声的产生。
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公开(公告)号：US08453454B2
公开(公告)日：2013-06-04
申请号：US12759794
申请日：2010-04-14
IPC分类号： F02C1/00
摘要： A premixer is provided and includes a peripheral wall defining a mixing chamber therein through which a flow path for a fluid is defined, a nozzle including an annular splitter plate disposed in the flow path within the mixing chamber, the splitter plate including a trailing edge defined in relation to a predominant direction of fluid flow along the flow path and being formed to define a fuel line therein, which is receptive of oil fuel and an annular array of fuel injectors disposed at the trailing edge, which are each fluidly communicative with the fuel line and configured to inject at least the oil fuel into the flow path with the oil fuel being substantially atomized upon injection or substantially immediately after the injection by interaction with the fluid flowing along the flow path.
摘要翻译： 提供预混合器并且包括在其中限定混合室的外围壁，通过该混合室限定用于流体的流动路径，喷嘴，其包括设置在混合室内的流动路径中的环形分离板，分离板包括限定的后缘 相对于沿着流动路径的流体流动的主要方向并且被形成为在其中限定其中容纳油燃料的燃料管线和设置在后缘处的燃料喷射器的环形阵列，其各自与燃料流体连通 并且构造成至少将油燃料喷射到流动路径中，其中油燃料在注射时基本上雾化，或者基本上在注射之后立即与沿着流动路径流动的流体相互作用。
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公开(公告)号：US08333075B2
公开(公告)日：2012-12-18
申请号：US12425293
申请日：2009-04-16
IPC分类号： F02C7/22
摘要： A system that includes a turbine fuel nozzle comprising an air-fuel premixer. The air-fuel premixed includes a swirl vane configured to swirl fuel and air in a downstream direction, wherein the swirl vane comprises an internal coolant path from a downstream end portion in an upstream direction through a substantial length of the swirl vane.
摘要翻译： 一种包括涡轮燃料喷嘴的系统，其包括空燃料预混合器。 空燃料预混合包括涡流叶片，其构造成沿下游方向旋转燃料和空气，其中涡流叶片包括从上游方向的下游端部通过旋转叶片的相当长度的内部冷却剂路径。
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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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