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公开(公告)号：US20130086914A1
公开(公告)日：2013-04-11
申请号：US13253298
申请日：2011-10-05
IPC分类号： F02C7/00
CPC分类号： F01D9/023 , F01D5/186 , F01D5/187 , F05D2300/6033
摘要： A turbine system is disclosed. The turbine system includes a transition duct having an inlet, an outlet, and a passage extending between the inlet and the outlet and defining a longitudinal axis, a radial axis, and a tangential axis. The outlet of the transition duct is offset from the inlet along the longitudinal axis and the tangential axis. The turbine system further includes a turbine section connected to the transition duct. The turbine section includes a plurality of shroud blocks at least partially defining a hot gas path, a plurality of buckets at least partially disposed in the hot gas path, and a plurality of nozzles at least partially disposed in the hot gas path. At least one of a shroud block, a bucket, or a nozzle includes means for withstanding high temperatures.
摘要翻译： 公开了一种涡轮机系统。 涡轮机系统包括具有入口，出口和在入口和出口之间延伸并限定纵向轴线，径向轴线和切向轴线的通道的过渡管道。 过渡管道的出口沿着纵向轴线和切线轴线从入口偏移。 涡轮机系统还包括连接到过渡管道的涡轮机部分。 涡轮部分包括至少部分地限定热气体路径的多个护罩块，至少部分地设置在热气体路径中的多个桶，以及至少部分地设置在热气体路径中的多个喷嘴。 护罩块，铲斗或喷嘴中的至少一个包括耐高温的装置。
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公开(公告)号：US10337404B2
公开(公告)日：2019-07-02
申请号：US12719674
申请日：2010-03-08
摘要： Turbine nozzle assemblies include a plurality of circumferentially spaced first components and second components, which are designed to provide different amounts of cooling. The second components, which are generally aligned with an opening of transition pieces, are designed to provide more cooling than the first components, which are generally aligned with interfaces between the transition pieces.
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公开(公告)号：US09506359B2
公开(公告)日：2016-11-29
申请号：US13437953
申请日：2012-04-03
IPC分类号： F01D9/02
CPC分类号： F01D9/023 , F05D2260/201 , F05D2260/202 , F23R3/002 , F23R3/06 , F23R2900/03042 , F23R2900/03044
摘要： The present application provides a combustion system for use with a cooling flow. The combustion system may include a head end, an aft end, a transition nozzle extending from the head end to the aft end, and an impingement sleeve surrounding the transition nozzle. The impingement sleeve may define a first cavity in communication with the head end for a first portion of the cooling flow and a second cavity in communication with the aft end for a second portion of the cooling flow. The transition nozzle may include a number of cooling holes thereon in communication with the second portion of the cooling flow.
摘要翻译： 本申请提供了一种用于冷却流的燃烧系统。 燃烧系统可以包括头端，后端，从头端延伸到后端的过渡喷嘴和围绕过渡喷嘴的冲击套筒。 冲击套筒可以限定与头端连通的用于冷却流的第一部分的第一空腔和与后端连通的用于冷却流的第二部分的第二空腔。 过渡喷嘴可以包括与冷却流的第二部分连通的多个冷却孔。
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公开(公告)号：US08683805B2
公开(公告)日：2014-04-01
申请号：US13567415
申请日：2012-08-06
申请人： Wei Chen , Kevin Weston McMahan
发明人： Wei Chen , Kevin Weston McMahan
CPC分类号： F02C7/22 , F01D11/003
摘要： An injector seal for a gas turbomachine includes a seal body having a first surface, an opposing second surface, a central opening configured and disposed to receive a gas turbomachine injector, an outer edge, and a plurality of passages extending through the seal body. The plurality of passages are configured and disposed to guide a fluid at the first surface through the second surface.
摘要翻译： 用于气体涡轮机的喷射器密封件包括密封体，其具有第一表面，相对的第二表面，中心开口，构造和设置成容纳气体涡轮机喷射器，外边缘和延伸穿过密封体的多个通道。 多个通道被构造和设置成引导第一表面处的流体穿过第二表面。
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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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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：US07082766B1
公开(公告)日：2006-08-01
申请号：US10906688
申请日：2005-03-02
摘要： A can combustor for an industrial turbine includes a transition piece transitioning directly from a combustor head-end to a turbine inlet using a single piece transition piece. In an exemplary embodiment, the transition piece is jointless.
摘要翻译： 用于工业涡轮机的罐式燃烧器包括使用单件式过渡件直接从燃烧器头端转换到涡轮入口的过渡件。 在示例性实施例中，过渡件是无接头的。
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公开(公告)号：US09255484B2
公开(公告)日：2016-02-09
申请号：US13049237
申请日：2011-03-16
CPC分类号： F01D9/023 , F01D25/12 , F02C7/20 , F05D2260/201 , F05D2260/202 , F05D2260/2322 , F23R3/60 , F23R2900/00012 , F23R2900/03041 , F23R2900/03042 , F23R2900/03043 , F23R2900/03044
摘要： An aft frame and a method for cooling an aft frame are disclosed. In one embodiment, an aft frame for a transition piece in a combustor is disclosed. The combustor includes the transition piece and an impingement sleeve at least partially defining a flow path therebetween. The aft frame includes a body and a generally radially extending cooling passage defined in the body, the cooling passage comprising a first end configured to accept a coolant. The aft frame further includes an exhaust passage defined in the body, the exhaust passage including a first end in communication with the cooling passage and a second end configured for communication with the flow path for flowing the coolant therethrough.
摘要翻译： 公开了一种后框架和用于冷却后框架的方法。 在一个实施例中，公开了一种用于燃烧室中的过渡件的后框架。 该燃烧器包括过渡件和至少部分地限定其间的流动路径的冲击套筒。 后框架包括主体和限定在主体中的大致径向延伸的冷却通道，冷却通道包括构造成接受冷却剂的第一端。 后框架还包括限定在主体中的排气通道，排气通道包括与冷却通道连通的第一端和构造成与用于使冷却剂流过的流路连通的第二端。
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公开(公告)号：US20130255262A1
公开(公告)日：2013-10-03
申请号：US13437954
申请日：2012-04-03
申请人： Won-Wook Kim , Kevin Weston McMahan
发明人： Won-Wook Kim , Kevin Weston McMahan
CPC分类号： F01D9/023 , F05D2250/14 , F23C5/08 , F23R3/46 , F23R2900/00014
摘要： The present application provides a combustor for use with a gas turbine engine. The combustor may include a head end with a non-circular configuration, a number of fuel nozzles positioned about the head end, and a transition piece extending downstream of the head end.
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。 燃烧器可以包括具有非圆形构造的头端，围绕头端定位的多个燃料喷嘴，以及在头端下游延伸的过渡件。
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