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公开(公告)号：US08926269B2
公开(公告)日：2015-01-06
申请号：US13225895
申请日：2011-09-06
CPC分类号： F01D11/001
摘要： A seal carrier for a seal used between rotating and non-rotating components includes an arcuate sheet metal seal carrier body formed to include a stepped, conical configuration wherein an inner diameter at a forward end is larger than the diameter at an aft end, with plural stepped sections defined by alternating radial and axial portions between the forward end and the aft end. Each axial portion is adapted to carry a seal element, preferably a honeycomb seal. Mounting flanges are provided at the forward end and the aft end of the arcuate sheet metal seal carrier body to enable attachment to the non-rotating component.
摘要翻译： 用于在旋转和非旋转部件之间使用的密封件的密封载体包括弓形金属片密封载体主体，其形成为包括阶梯状锥形结构，其中前端的内径大于后端的直径，多个 在前端和后端之间由交替的径向和轴向部分限定的台阶部分。 每个轴向部分适于承载密封元件，优选地是蜂窝密封件。 安装凸缘设置在弓形金属密封载体主体的前端和后端，以能够连接到非旋转部件。
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公开(公告)号：US20120297792A1
公开(公告)日：2012-11-29
申请号：US13117199
申请日：2011-05-27
CPC分类号： F01D17/085 , Y10T29/4932
摘要： A turbomachine includes a nozzle. The nozzle includes an end portion and an airfoil portion. A diaphragm is mounted to the end portion of the nozzle in a wheel space portion of the turbomachine. The diaphragm includes an external surface and an internal surface. The diaphragm also includes at least one thermocouple well receiving portion formed in one of the external surface and the internal surface. A thermocouple well is mounted in the at least one thermocouple well receiving portion. The thermocouple well includes a first end exposed to the wheel space portion of the turbomachine and a second end exposed at the internal surface of the diaphragm.
摘要翻译： 涡轮机包括喷嘴。 喷嘴包括端部和翼型部。 在涡轮机的车轮空间部分中将隔膜安装到喷嘴的端部。 隔膜包括外表面和内表面。 隔膜还包括形成在外表面和内表面之一中的至少一个热电偶阱接收部分。 热电偶阱安装在至少一个热电偶阱接收部分中。 热电偶阱包括暴露于涡轮机的轮空间部分的第一端和暴露在隔膜内表面的第二端。
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公开(公告)号：US20130111912A1
公开(公告)日：2013-05-09
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
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 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：US09038394B2
公开(公告)日：2015-05-26
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
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：US20130283817A1
公开(公告)日：2013-10-31
申请号：US13459501
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 , F05D2300/10 , F05D2300/501 , F05D2300/6012
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 flexible seal contacting the interface feature to provide a seal between the interface feature and the adjacent transition duct. The flexible seal includes a sheet having a first surface, an opposing second surface, and a peripheral edge therebetween.
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柔性密封件，以在接口特征和相邻的过渡管道之间提供密封。 柔性密封件包括具有第一表面，相对的第二表面和它们之间的周边边缘的片材。
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公开(公告)号：US20130269821A1
公开(公告)日：2013-10-17
申请号：US13446831
申请日：2012-04-13
CPC分类号： F01D9/023 , F05D2250/70 , Y10T29/49
摘要： Disclosed herein are methods, systems, and apparatuses for hot gas flow. In an embodiment, a transition piece comprises a surface that conforms to an approximately straight line path stretching approximately from the forward end of a transition piece to the aft end of the transition piece wherein the surface may help direct the flow of gases.
摘要翻译： 本文公开了用于热气流的方法，系统和装置。 在一个实施例中，过渡件包括符合近似直线路径的表面，其大致从过渡件的前端延伸到过渡件的后端，其中表面可以帮助引导气体流动。
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公开(公告)号：US08459041B2
公开(公告)日：2013-06-11
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
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：US09328623B2
公开(公告)日：2016-05-03
申请号：US13253298
申请日：2011-10-05
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：US08827641B2
公开(公告)日：2014-09-09
申请号：US13304720
申请日：2011-11-28
CPC分类号： F01D9/02 , F01D1/04 , F01D5/142 , F05D2250/74
摘要： A turbine nozzle is provided including a nozzle airfoil having an airfoil shape, the nozzle airfoil having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table 1 wherein the Cartesian coordinate values of X, Y and Z are non-dimensional values from 0% to 100% convertible to dimensional distances in inches by multiplying the Cartesian coordinate values of X, Y and Z by a height of the airfoil in inches, and wherein X and Y are distances in inches which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z, the airfoil profile sections at Z distances being joined smoothly with one another to form a complete airfoil shape.
摘要翻译： 提供了一种涡轮喷嘴，其包括具有翼型形状的喷嘴翼型，喷嘴翼型件具有基本上符合表1所示的X，Y和Z的笛卡尔坐标值的标称轮廓，其中X，Y和Z的笛卡尔坐标值 是通过将X，Y和Z的笛卡尔坐标值乘以翼型的高度（英寸），其中X和Y是以英寸为单位的距离，其中，当 通过平滑连续的弧连接，在每个距离Z处限定翼型轮廓部分，Z距离处的翼型轮廓部分彼此平滑地连接以形成完整的翼型形状。
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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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