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公开(公告)号：US20100205972A1
公开(公告)日：2010-08-19
申请号：US12372246
申请日：2009-02-17
IPC分类号： F02C7/12
摘要： A method, system, and apparatus is provided for transferring heat from a can combustor associated with a gas turbine by providing a one-piece can combustor body having surface features that facilitate the transfer of heat away from the can combustor body, and by directing air flow to the surface features so that heat from the can combustor body is transferred from the surface features to the air flow.
摘要翻译： 提供了一种方法，系统和装置，用于通过提供具有便于将热量从罐式燃烧器主体传递的表面特征的一体式罐式燃烧器主体，以及通过引导空气 流到表面特征，使得来自罐式燃烧器主体的热量从表面特征传递到气流。
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公开(公告)号：US20120031097A1
公开(公告)日：2012-02-09
申请号：US13263995
申请日：2009-05-07
申请人： Kevin Weston McMahan , Krishna Kumar Venkataraman , Jonathan Dwight Berry , Sergey Aleksandrovich Stryapuninr
发明人： Kevin Weston McMahan , Krishna Kumar Venkataraman , Jonathan Dwight Berry , Sergey Aleksandrovich Stryapuninr
CPC分类号： F23R3/286 , F23C7/004 , F23C2900/07001 , F23D14/64 , F23D2900/14021
摘要： The present application provides a fuel nozzle for use in a gas turbine. The fuel nozzle may include a mounting flange, a number of premixers attached to each other, and a number of gas pathways extending from the mounting flange to the number of premixers.
摘要翻译： 本申请提供了一种用于燃气轮机的燃料喷嘴。 燃料喷嘴可以包括安装凸缘，彼此连接的多个预混合器以及从安装法兰延伸到预混合器的数量的多个气体通路。
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公开(公告)号：US20100293955A1
公开(公告)日：2010-11-25
申请号：US12469507
申请日：2009-05-20
IPC分类号： F02C7/22
摘要： A system comprising a fuel nozzle. The fuel nozzle includes a mounting base and an inlet flow conditioner extending directly from the mounting base in a downstream direction. Moreover, the inlet flow conditioner structurally supports the fuel nozzle without a central support member extending directly from the mounting base inside the inlet flow conditioner.
摘要翻译： 一种包括燃料喷嘴的系统。 燃料喷嘴包括安装基座和沿着下游方向从安装基座直接延伸的入口流动调节器。 此外，入口流动调节器结构地支撑燃料喷嘴，而没有直接从入口流动调节器内的安装基座延伸的中心支撑构件。
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公开(公告)号：US20120328421A1
公开(公告)日：2012-12-27
申请号：US13164887
申请日：2011-06-21
CPC分类号： F01D9/023 , F05D2260/20 , F23R3/002 , F23R3/06 , F23R3/346 , F23R2900/03041 , F23R2900/03042 , Y02T50/675 , Y10T29/4932 , Y10T29/49323
摘要： A turbine assembly includes a fuel nozzle configured to mix fuel and air and a transition nozzle oriented to receive the fuel and air mixture from the fuel nozzle. The transition nozzle includes a transition portion and a nozzle portion integrally formed with the transition portion. The transition nozzle includes a plurality of openings oriented to channel air to facilitate cooling the transition portion and/or the nozzle portion. The transition portion is oriented to channel combustion gases towards the nozzle portion.
摘要翻译： 涡轮组件包括构造成混合燃料和空气的燃料喷嘴和定向成从燃料喷嘴接收燃料和空气混合物的过渡喷嘴。 过渡喷嘴包括过渡部分和与过渡部分一体形成的喷嘴部分。 过渡喷嘴包括定向成引导空气以便于冷却过渡部分和/或喷嘴部分的多个开口。 过渡部分被定向成将燃烧气体引向喷嘴部分。
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公开(公告)号：US20100218502A1
公开(公告)日：2010-09-02
申请号：US12395739
申请日：2009-03-02
IPC分类号： F23R3/42
CPC分类号： F23R3/06 , F23R3/002 , F23R3/005 , F23R3/46 , F23R2900/03041
摘要： A combustor for an industrial turbine includes a single transition piece transitioning directly from a combustor head-end to a turbine inlet. The transition piece includes an inner surface and an outer surface. The inner surface bounds an interior space for combusted gas flow from the combustor head-end to the turbine inlet. The outer surface at least partially defines an area for compressor discharge air flow. The transition piece includes a plurality of apertures configured to allow compressor discharge air flow into the interior space. Each of the plurality of apertures extends from an entry portion on the outer surface to an exit portion on the inner surface.
摘要翻译： 用于工业涡轮机的燃烧器包括直接从燃烧器头端转换到涡轮机入口的单个过渡件。 过渡件包括内表面和外表面。 内表面限定用于从燃烧器头端到涡轮机入口的燃烧气体流的内部空间。 外表面至少部分地限定用于压缩机排出气流的区域。 过渡件包括多个孔，其构造成允许压缩机排出空气流入内部空间。 多个孔中的每一个从外表面上的入口部分延伸到内表面上的出口部分。
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6.发明申请公开(公告)号：US20100300106A1
公开(公告)日：2010-12-02
申请号：US12476926
申请日：2009-06-02
IPC分类号： F02C1/00
CPC分类号： F23R3/10 , F23R2900/03041
摘要： A system comprises a turbine combustor cap. The turbine combustor cap includes a plurality of segments. Each segment of the plurality of segments has edges abutting at least two fuel nozzle receptacles. Moreover, each segment of the plurality of segments does not completely surrounding any one fuel nozzle receptacle.
摘要翻译： 一种系统包括涡轮机燃烧器盖。 涡轮机燃烧器盖包括多个段。 多个段的每个段具有邻接至少两个燃料喷嘴容器的边缘。 此外，多个段的每个段都不完全围绕任何一个燃料喷嘴容器。
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公开(公告)号：US08707705B2
公开(公告)日：2014-04-29
申请号：US12553153
申请日：2009-09-03
IPC分类号： F02C7/12
CPC分类号： F23R3/002 , F01D9/023 , F23R2900/03043 , F23R2900/03044
摘要： An aft frame of a turbine engine transition piece body is provided and includes an annular body disposed within a first annular space defined between an impingement sleeve and a compressor discharge casing and aft of a second annular space defined between the transition piece body and the impingement sleeve and including a main portion with a first surface facing the first annular space and a second surface facing the forward annular space. The main portion has an impingement hole extending therethrough from an inlet at the first surface of the annular body to an outlet at the second surface of the annular body to define a fluid path along which the first and second annular spaces communicate with one another.
摘要翻译： 提供了一种涡轮发动机过渡件本体的后框架，并且包括设置在限定在冲击套筒和压缩机排出壳体之间的第一环形空间内的环形体，以及限定在过渡件主体和冲击套筒之间的第二环形空间的后部 并且包括具有面向第一环形空间的第一表面的主要部分和面向前部环形空间的第二表面。 主要部分具有从环形体的第一表面处的入口延伸到环形体的第二表面处的出口的冲击孔，以限定第一和第二环形空间彼此连通的流体路径。
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8.发明授权公开(公告)号：US08495881B2
公开(公告)日：2013-07-30
申请号：US12476926
申请日：2009-06-02
IPC分类号： F02C1/00
CPC分类号： F23R3/10 , F23R2900/03041
摘要： A system comprises a turbine combustor cap. The turbine combustor cap includes a plurality of segments. Each segment of the plurality of segments has edges abutting at least two fuel nozzle receptacles. Moreover, each segment of the plurality of segments does not completely surrounding any one fuel nozzle receptacle.
摘要翻译： 一种系统包括涡轮机燃烧器盖。 涡轮机燃烧器盖包括多个段。 多个段的每个段具有邻接至少两个燃料喷嘴容器的边缘。 此外，多个段的每个段都不完全围绕任何一个燃料喷嘴容器。
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9.发明申请COMBUSTOR ASSEMBLY FOR USE IN A TURBINE ENGINE AND METHODS OF ASSEMBLING SAME 审中-公开用于涡轮发动机的燃烧器组件及其装配方法公开(公告)号：US20120324898A1
公开(公告)日：2012-12-27
申请号：US13164948
申请日：2011-06-21
CPC分类号： F23R3/002 , F01D9/023 , F23R3/425 , F23R2900/03044 , Y10T29/49348
摘要： A combustor assembly for use with a turbine engine that includes a rotor assembly. The combustor assembly includes a casing that includes a plenum and a combustor liner that is spaced a distance from the plenum and that defines a combustion chamber therein. A transition nozzle extends between the combustor liner and the rotor assembly for channeling combustion gases from the combustion chamber to the rotor assembly. The transition nozzle includes a transition portion and a nozzle portion integrally formed with the transition portion. An annular flowsleeve is coupled radially outward from the transition nozzle such that an annular flow path is defined between the flowsleeve and the transition nozzle. The flowsleeve includes a plurality of openings extending through an outer surface of the flowsleeve for providing flow communication between the plenum and the annular flow path to facilitate impingement cooling of the flowsleeve.
摘要翻译： 一种与包括转子组件的涡轮发动机一起使用的燃烧器组件。 燃烧器组件包括壳体，其包括气室和与集气室隔开一定距离且在其中限定燃烧室的燃烧器衬套。 过渡喷嘴在燃烧器衬套和转子组件之间延伸，用于将燃烧气体从燃烧室引导至转子组件。 过渡喷嘴包括过渡部分和与过渡部分一体形成的喷嘴部分。 环形流动体从过渡喷嘴径向向外耦合，使得在流动流体和过渡喷嘴之间限定环形流动路径。 流动通道包括延伸穿过流动的外表面的多个开口，用于提供气室与环形流路之间的流动连通，以便于流动的冲击冷却。
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公开(公告)号：US08522555B2
公开(公告)日：2013-09-03
申请号：US12469507
申请日：2009-05-20
IPC分类号： F23R3/14
摘要： A system comprising a fuel nozzle. The fuel nozzle includes a mounting base and an inlet flow conditioner extending directly from the mounting base in a downstream direction. Moreover, the inlet flow conditioner structurally supports the fuel nozzle without a central support member extending directly from the mounting base inside the inlet flow conditioner.
摘要翻译： 一种包括燃料喷嘴的系统。 燃料喷嘴包括安装基座和沿着下游方向从安装基座直接延伸的入口流动调节器。 此外，入口流动调节器结构地支撑燃料喷嘴，而没有直接从入口流动调节器内的安装基座延伸的中心支撑构件。
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