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公开(公告)号：US20120186260A1
公开(公告)日：2012-07-26
申请号：US13012838
申请日：2011-01-25
IPC分类号： F01D25/24
CPC分类号： F01D9/023
摘要： An impingement sleeve for a transition piece of a gas turbine is disclosed. The impingement sleeve generally includes a first casing configured to surround a portion of an inner duct of the transition piece and a second casing configured to surround a portion of the inner duct. Additionally, the impingement sleeve may include a joint defined between the first and second casings. The joint may include a plurality of fasteners configured to attach the first casing to the second casing.
摘要翻译： 公开了一种用于燃气轮机的过渡件的冲击套筒。 冲击套管通常包括构造成围绕过渡件的内部管道的一部分的第一壳体和被构造成围绕内部管道的一部分的第二壳体。 此外，冲击套筒可以包括限定在第一和第二壳体之间的接头。 接头可以包括被配置成将第一壳体附接到第二壳体的多个紧固件。
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公开(公告)号：US20110271688A1
公开(公告)日：2011-11-10
申请号：US12774822
申请日：2010-05-06
IPC分类号： F02C7/20
摘要： A transition piece support for a turbomachine includes one or more support arms extending across a diffuser flowpath to the transition piece. The one or more support arms include a streamwise surface and a crosswise surface. A streamwise extent of the streamwise surface is greater than a crosswise extent of the crosswise surface to reduce flow anomalies in a flow of fluid across the one or more support arms. A turbomachine includes a combustor, a diffuser, a transition piece operably connected to the combustor and a transition piece support including one or more support arms extending across a flow of fluid to the transition piece. The support arms include a streamwise surface and a crosswise surface. A streamwise extent of the streamwise surface is greater than a crosswise extent of the crosswise surface to reduce flow anomalies in a flow of fluid across the one or more support arms.
摘要翻译： 用于涡轮机的过渡件支撑件包括一个或多个支撑臂，跨越扩散器流动路径延伸到过渡件。 一个或多个支撑臂包括流动表面和横向表面。 流动表面的流动范围大于横向表面的横向范围，以减少穿过一个或多个支撑臂的流体流中的流量异常。 涡轮机包括燃烧器，扩散器，可操作地连接到燃烧器的过渡件和过渡件支撑件，该过渡件支撑件包括跨过流体流延伸到过渡件的一个或多个支撑臂。 支撑臂包括流动表面和横向表面。 流动表面的流动范围大于横向表面的横向范围，以减少穿过一个或多个支撑臂的流体流中的流量异常。
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公开(公告)号：US08701415B2
公开(公告)日：2014-04-22
申请号：US13292389
申请日：2011-11-09
申请人： James Scott Flanagan , Jeffrey Scott LeBegue , Kevin Weston McMahan , Daniel Jackson Dillard , Ronnie Ray Pentecost
发明人： James Scott Flanagan , Jeffrey Scott LeBegue , Kevin Weston McMahan , Daniel Jackson Dillard , Ronnie Ray Pentecost
CPC分类号： F01D9/023 , F01D11/005 , F05D2240/57
摘要： A turbine system is disclosed. In one embodiment, the turbine system includes a transition duct. The transition duct includes 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 transition duct further includes an interface member for interfacing with a turbine section. The turbine system further includes a flexible metallic seal contacting the interface member to provide a seal between the interface member and the turbine section.
摘要翻译： 公开了一种涡轮机系统。 在一个实施例中，涡轮机系统包括过渡管道。 过渡管道包括入口，出口和在入口和出口之间延伸并且限定纵向轴线，径向轴线和切线轴线的通道。 过渡管道的出口沿着纵向轴线和切线轴线从入口偏移。 过渡管道还包括用于与涡轮部分相接合的接口部件。 涡轮机系统还包括接触接口构件的柔性金属密封件，以在接口构件和涡轮部分之间提供密封。
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公开(公告)号：US08974179B2
公开(公告)日：2015-03-10
申请号：US13292351
申请日：2011-11-09
申请人： James Scott Flanagan , Jeffrey Scott LeBegue , Kevin Weston McMahan , Daniel Jackson Dillard , Ronnie Ray Pentecost
发明人： James Scott Flanagan , Jeffrey Scott LeBegue , Kevin Weston McMahan , Daniel Jackson Dillard , Ronnie Ray Pentecost
CPC分类号： F01D9/023 , F01D11/003 , F16J15/0887
摘要： A turbine system is disclosed. In one embodiment, the turbine system includes a transition duct. The transition duct includes 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 transition duct further includes an interface member for interfacing with a turbine section. The turbine system further includes a convolution seal contacting the interface member to provide a seal between the interface member and the turbine section.
摘要翻译： 公开了一种涡轮机系统。 在一个实施例中，涡轮机系统包括过渡管道。 过渡管道包括入口，出口和在入口和出口之间延伸并且限定纵向轴线，径向轴线和切线轴线的通道。 过渡管道的出口沿着纵向轴线和切线轴线从入口偏移。 过渡管道还包括用于与涡轮部分相接合的接口部件。 涡轮机系统还包括与接口构件接触以在接口构件和涡轮机段之间提供密封的卷积密封件。
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公开(公告)号：US20130283818A1
公开(公告)日：2013-10-31
申请号：US13459533
申请日：2012-04-30
申请人： James Scott Flanagan , Jeffrey Scott LeBegue , Kevin Weston McMahan , Daniel Jackson Dillard , Ronnie Ray Pentecost
发明人： James Scott Flanagan , Jeffrey Scott LeBegue , Kevin Weston McMahan , Daniel Jackson Dillard , Ronnie Ray Pentecost
IPC分类号： F02C7/28
CPC分类号： F01D9/023 , F01D11/005 , F05D2240/55 , F05D2250/183 , F05D2300/10 , F05D2300/501 , F23R3/002
摘要： A turbine system is disclosed. In one embodiment, the turbine system includes a transition duct. The transition duct includes 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 transition duct further includes an interface feature for interfacing with an adjacent transition duct. The turbine system further includes a convolution seal contacting the interface feature to provide a seal between the interface feature and the adjacent transition duct.
摘要翻译： 公开了一种涡轮机系统。 在一个实施例中，涡轮机系统包括过渡管道。 过渡管道包括入口，出口和在入口和出口之间延伸并且限定纵向轴线，径向轴线和切线轴线的通道。 过渡管道的出口沿着纵向轴线和切线轴线从入口偏移。 过渡管道还包括用于与相邻过渡管道相连接的界面特征。 涡轮机系统还包括接触接口特征的卷积密封件，以在接口特征和相邻的过渡管道之间提供密封。
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公开(公告)号：US20130115048A1
公开(公告)日：2013-05-09
申请号：US13292351
申请日：2011-11-09
申请人： James Scott Flanagan , Jeffrey Scott LeBegue , Kevin Weston McMahan , Daniel Jackson Dillard , Ronnie Ray Pentecost
发明人： James Scott Flanagan , Jeffrey Scott LeBegue , Kevin Weston McMahan , Daniel Jackson Dillard , Ronnie Ray Pentecost
CPC分类号： F01D9/023 , F01D11/003 , F16J15/0887
摘要： A turbine system is disclosed. In one embodiment, the turbine system includes a transition duct. The transition duct includes 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 transition duct further includes an interface member for interfacing with a turbine section. The turbine system further includes a convolution seal contacting the interface member to provide a seal between the interface member and the turbine section.
摘要翻译： 公开了一种涡轮机系统。 在一个实施例中，涡轮机系统包括过渡管道。 过渡管道包括入口，出口和在入口和出口之间延伸并且限定纵向轴线，径向轴线和切线轴线的通道。 过渡管道的出口沿着纵向轴线和切线轴线从入口偏移。 过渡管道还包括用于与涡轮部分相接合的接口部件。 涡轮机系统还包括与接口构件接触以在接口构件和涡轮机段之间提供密封的卷积密封件。
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公开(公告)号：US20130111911A1
公开(公告)日：2013-05-09
申请号：US13292366
申请日：2011-11-09
申请人： James Scott Flanagan , Jeffrey Scott LeBegue , Kevin Weston McMahan , Daniel Jackson Dillard , Ronnie Ray Pentecost
发明人： James Scott Flanagan , Jeffrey Scott LeBegue , Kevin Weston McMahan , Daniel Jackson Dillard , Ronnie Ray Pentecost
IPC分类号： F23R3/42
CPC分类号： F01D9/023 , F01D11/005 , F05D2240/57
摘要： A turbine system is disclosed. In one embodiment, the turbine system includes a transition duct. The transition duct includes 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 transition duct further includes an interface member for interfacing with a turbine section. The turbine system further includes a leaf seal contacting the interface member to provide a seal between the interface member and the turbine section.
摘要翻译： 公开了一种涡轮机系统。 在一个实施例中，涡轮机系统包括过渡管道。 过渡管道包括入口，出口和在入口和出口之间延伸并且限定纵向轴线，径向轴线和切线轴线的通道。 过渡管道的出口沿着纵向轴线和切线轴线从入口偏移。 过渡管道还包括用于与涡轮部分相接合的接口部件。 涡轮机系统还包括接触接口构件的叶片密封件，以在接口构件和涡轮机部分之间提供密封。
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公开(公告)号：US09133722B2
公开(公告)日：2015-09-15
申请号：US13459516
申请日：2012-04-30
申请人： Jeffrey Scott LeBegue , Ronnie Ray Pentecost , James Scott Flanagan , Won-Wook Kim , Kevin Weston McMahan
发明人： Jeffrey Scott LeBegue , Ronnie Ray Pentecost , James Scott Flanagan , Won-Wook Kim , Kevin Weston McMahan
摘要： A system for supplying an injection fluid to a combustor is disclosed. The system includes a transition duct comprising 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 passage defines a combustion chamber. The system further includes a tube providing fluid communication for the injection fluid to flow through the transition duct and into the combustion chamber.
摘要翻译： 公开了一种用于向燃烧器供应喷射流体的系统。 该系统包括过渡管道，其包括入口，出口和在入口和出口之间延伸并且限定纵向轴线，径向轴线和切线轴线的通道。 过渡管道的出口沿着纵向轴线和切线轴线从入口偏移。 通道限定燃烧室。 该系统还包括提供流体连通的管，用于使注射流体流过过渡管并进入燃烧室。
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公开(公告)号：US08978388B2
公开(公告)日：2015-03-17
申请号：US13152638
申请日：2011-06-03
CPC分类号： F23R3/425 , F01D9/023 , F01D25/28 , F05D2250/314 , F05D2260/30 , F23R3/002 , F23R3/60
摘要： A loading assembly for a turbine system is disclosed. The loading assembly includes a transition duct and a load member. The transition duct extends between a fuel nozzle and a turbine section, and has 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 load member extends from the transition duct and is configured to transfer a load between the transition duct and an adjacent transition duct along at least one of the longitudinal axis, the radial axis, or the tangential axis.
摘要翻译： 公开了一种用于涡轮机系统的装载组件。 装载组件包括过渡管道和负载构件。 过渡管道在燃料喷嘴和涡轮机部分之间延伸，并且具有入口，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。 过渡管道的出口沿着纵向轴线和切线轴线从入口偏移。 负载构件从过渡管道延伸并且构造成沿着纵向轴线，径向轴线或切线轴线中的至少一个在过渡管道和相邻过渡管道之间传递负载。
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公开(公告)号：US08448450B2
公开(公告)日：2013-05-28
申请号：US13176166
申请日：2011-07-05
IPC分类号： F02C7/20
CPC分类号： F01D9/023 , F02C3/14 , F05D2250/40
摘要： A support assembly for a turbine system is disclosed. The support assembly includes a transition duct extending between a fuel nozzle and a turbine section. The transition duct has 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. The support assembly further includes a plurality of protrusions extending from the transition duct. The plurality of protrusions are configured to allow movement of the transition duct about at least one axis.
摘要翻译： 公开了一种用于涡轮机系统的支撑组件。 支撑组件包括在燃料喷嘴和涡轮部分之间延伸的过渡管道。 过渡管道具有入口，出口和在入口和出口之间延伸并且限定纵向轴线，径向轴线和切线轴线的通道。 过渡管道的出口沿着纵向轴线从进口偏移。 支撑组件还包括从过渡管道延伸的多个突起。 多个突起构造成允许过渡管道围绕至少一个轴线移动。
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