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公开(公告)号：US06854961B2
公开(公告)日：2005-02-15
申请号：US10446688
申请日：2003-05-29
CPC分类号： F01D5/141 , F05D2220/3212 , F05D2240/301 , F05D2250/74 , Y10S416/02
摘要： First stage turbine buckets have airfoil profiles substantially in accordance with Cartesian coordinate values of X, Y and Z set forth Table I wherein X and Y values are in inches and the Z values are non-dimensional values from 0 to 1 convertible to Z distances in inches by multiplying the Z values by the height of the airfoil in inches. The X and Y values are distances which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z. The profile sections at each distance Z are joined smoothly to one another to form a complete airfoil shape. The X, Y and Z distances may be scalable as a function of the same constant or number to provide a scaled up or scaled down airfoil section for the bucket. The nominal airfoil given by the X, Y and Z distances lies within an envelop of ±0.055 inches in directions normal to the surface of the airfoil.
摘要翻译： 第一级涡轮机叶片具有基本上符合X，Y和Z的笛卡尔坐标值的翼型轮廓，其中X和Y值以英寸计，Z值是从0到1可转换成Z距离的无量纲值 将Z值乘以翼型件的高度（英寸）。 X和Y值是通过平滑连续弧连接时定义每个距离Z处的翼型轮廓部分的距离。每个距离Z处的轮廓部分彼此平滑地连接以形成完整的翼型形状。 X，Y和Z距离可以作为相同常数或数字的函数来缩放，以提供用于铲斗的放大或缩小的翼型部分。 由X，Y和Z距离给出的标称翼型在垂直于翼面表面的方向上处于±0.055英寸的包络内。
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公开(公告)号：US06893210B2
公开(公告)日：2005-05-17
申请号：US10684402
申请日：2003-10-15
CPC分类号： F01D5/141 , F01D5/18 , F01D5/187 , Y10S416/02
摘要： First stage turbine buckets have internal core profiles substantially in accordance with Cartesian coordinate values of X, Y and Z set forth Table I wherein X and Y values are in inches and the Z values are non-dimensional values convertible to Z distances in inches by multiplying the Z values by the height of the airfoil in inches. The X and Y values are distances which, when connected by smooth continuing arcs, define internal core profile sections at each distance Z. The profile sections at each distance Z are joined smoothly to one another to form a complete internal core profile. The X, Y and Z distances may be scalable as a function of the same constant or number to provide a scaled up or scaled down internal core profile. The nominal internal core profile given by the X, Y and Z distances lies within an envelope of ±0.050 inches in directions normal to any internal core surface location.
摘要翻译： 第一级涡轮机桶具有基本上根据X，Y和Z的笛卡尔坐标值的内部芯轮廓，其中X和Y和Z表示在表I中，其中X和Y值以英寸为单位，Z值是通过乘以可以以英寸换算为Z距离的无量纲值 Z值以翼型的高度为单位。 X和Y值是当通过光滑连续弧连接时，在每个距离Z处限定内部芯轮廓部分的距离。每个距离Z处的轮廓部分彼此平滑地连接以形成完整的内部芯轮廓。 X，Y和Z距离可以是可扩展的，作为相同常数或数字的函数，以提供按比例放大或缩小的内核配置文件。 由X，Y和Z距离给出的标称内芯型材位于垂直于任何内芯表面位置的方向内的±0.050英寸的包络内。
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公开(公告)号：US09297262B2
公开(公告)日：2016-03-29
申请号：US13479683
申请日：2012-05-24
申请人： Xiuzhang James Zhang , Aaron Ezekiel Smith , Anthony Louis Giglio , Brian Peter Arness , Benjamin Paul Lacy
发明人： Xiuzhang James Zhang , Aaron Ezekiel Smith , Anthony Louis Giglio , Brian Peter Arness , Benjamin Paul Lacy
摘要： A turbine rotor blade for a gas turbine engine is described. The turbine rotor blade includes an airfoil that includes a tip at an outer radial end. The tip includes a rail that defines a tip cavity; and the rail includes a circumscribing rail microchannel. The circumscribing rail microchannel is a microchannel that extends around at least a majority of the length of the inner rail surface.
摘要翻译： 描述了一种用于燃气涡轮发动机的涡轮转子叶片。 涡轮转子叶片包括在外径向端部包括尖端的翼型件。 尖端包括限定尖端腔的轨道; 并且轨道包括外接轨道微通道。 外接导轨微通道是围绕内轨表面的至少大部分长度延伸的微通道。
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公开(公告)号：US20140030101A1
公开(公告)日：2014-01-30
申请号：US13558659
申请日：2012-07-26
IPC分类号： F03B3/12
CPC分类号： F01D5/20 , F05D2260/201
摘要： A turbine bucket having an airfoil is disclosed. The airfoil may include a pressure side wall and a suction side wall extending between a leading edge and a trailing edge. In addition, the airfoil may include a base and a tip disposed opposite the base. The tip may include a tip floor and pressure and suction side tip walls extending outwardly from the tip floor. Moreover, the tip may include an intermediate tip wall extending outwardly from the tip floor between the pressure and suction side tip walls. The intermediate tip wall may define a height that is less than a height of the pressure and/or suction side tip walls.
摘要翻译： 公开了一种具有翼型的涡轮机桶。 翼型件可以包括在前缘和后缘之间延伸的压力侧壁和吸力侧壁。 此外，翼型件可以包括基部和与基部相对设置的尖端。 尖端可以包括尖端地板和从尖端底板向外延伸的压力和吸力侧尖端壁。 此外，尖端可以包括在压力侧和吸力侧尖端壁之间从尖端地板向外延伸的中间尖端壁。 中间尖端壁可以限定小于压力和/或吸力侧尖端壁的高度的高度。
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公开(公告)号：US20130195650A1
公开(公告)日：2013-08-01
申请号：US13359691
申请日：2012-01-27
IPC分类号： F01D5/18
CPC分类号： F01D5/187 , F05D2240/303 , F05D2250/25 , F05D2260/202
摘要： A turbine airfoil includes a blade having a leading and trailing edges and an internal cooling circuit, and a plurality of film holes extending between the internal cooling circuit and an exterior of the blade. The plurality of film holes are shaped to generate a swirling flow exiting the film holes adjacent the leading edge to thereby enhance local convection and provide an insulating barrier to gaspath flow.
摘要翻译： 涡轮机翼片包括具有前缘和后缘以及内部冷却回路的叶片，以及在内部冷却回路和叶片的外部之间延伸的多个薄膜孔。 多个膜孔被成形为产生离开前缘的膜孔的旋流，从而增强局部对流，并为气路流动提供绝缘屏障。
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公开(公告)号：US09470096B2
公开(公告)日：2016-10-18
申请号：US13558685
申请日：2012-07-26
CPC分类号： F01D5/20 , F05D2250/23 , F05D2250/231 , F05D2250/232 , F05D2260/202
摘要： A turbine bucket having an airfoil is disclosed. The airfoil may include a pressure side and a suction side extending between a leading edge and a trailing edge. In addition, the airfoil may include a tip. The tip may include a tip floor and a tip wall extending outwardly from the tip floor. The tip wall may include an inner surface defining an inner perimeter of the tip wall. Moreover, a plurality of notches may be defined by the inner surface around at least a portion of the inner perimeter.
摘要翻译： 公开了一种具有翼型的涡轮机桶。 翼型件可以包括在前缘和后缘之间延伸的压力侧和吸力侧。 此外，翼型件可以包括尖端。 尖端可以包括尖端地板和从尖端底板向外延伸的尖端壁。 尖端壁可以包括限定尖端壁的内周边的内表面。 此外，多个凹口可以由围绕内周边的至少一部分的内表面限定。
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公开(公告)号：US20110236183A1
公开(公告)日：2011-09-29
申请号：US12731186
申请日：2010-03-25
CPC分类号： F16J15/0887 , F01D11/005 , F05D2300/50212
摘要： A spline seal for a hot gas path component is provided. The spline seal may include a first metal layer and a second metal layer. The first metal layer may have a first volumetric thermal expansion coefficient. The second metal layer may be disposed adjacent the first metal layer and have a second volumetric thermal expansion coefficient. The second volumetric thermal expansion coefficient may be higher than the first volumetric thermal expansion coefficient. When the spline seal is exposed to a heat source, the first and second metal layers may deform to provide a seal between the hot gas path component and an adjacent hot gas path component.
摘要翻译： 提供了用于热气路径部件的花键密封。 花键密封件可以包括第一金属层和第二金属层。 第一金属层可以具有第一体积热膨胀系数。 第二金属层可以邻近第一金属层设置并具有第二体积热膨胀系数。 第二体积热膨胀系数可以高于第一体积热膨胀系数。 当花键密封件暴露于热源时，第一和第二金属层可以变形以在热气体路径部件和相邻的热气体通道部件之间提供密封。
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公开(公告)号：US20140064984A1
公开(公告)日：2014-03-06
申请号：US13600782
申请日：2012-08-31
申请人： Xiuzhang James Zhang , Camilo Andres Sampayo , Adebukola Oluwaseun Benson , Christopher William Kester
发明人： Xiuzhang James Zhang , Camilo Andres Sampayo , Adebukola Oluwaseun Benson , Christopher William Kester
IPC分类号： F01D5/18
CPC分类号： F01D5/18 , F01D5/187 , F05D2240/81 , Y02T50/676
摘要： A platform cooling arrangement in a turbine rotor blade having a platform at an interface between an airfoil and a root. The platform may include a pressure side slashface and a suction side slashface. The platform cooling arrangement may include: a cooling channel formed within the interior of the platform, the cooling channel extending from a first end toward one of the pressure side slashface and the suction side slashface. At a second end, the cooling channel may include a pocket. The pocket may include an abrupt increase in cross-sectional flow area just before the cooling channel reaches the slashface.
摘要翻译： 涡轮转子叶片中的平台冷却装置，其具有在翼型件和根部之间的界面处的平台。 平台可以包括压力侧斜面和吸力侧斜面。 平台冷却装置可以包括：形成在平台内部的冷却通道，冷却通道从第一端向压力侧斜面和吸力侧斜面之一延伸。 在第二端，冷却通道可以包括口袋。 袋子可能包括在冷却通道到达斜面之前的横截面流动区域的突然增加。
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公开(公告)号：US20130315748A1
公开(公告)日：2013-11-28
申请号：US13479663
申请日：2012-05-24
IPC分类号： F01D5/18
CPC分类号： F01D5/20 , F01D5/186 , F05D2260/204
摘要： A turbine rotor blade used in a gas turbine engine, which includes an airfoil having a tip at an outer radial edge, is described. The airfoil includes a pressure sidewall and a suction sidewall that join together at a leading edge and a trailing edge of the airfoil, the pressure sidewall and the suction sidewall extending from a root to the tip. The tip includes a tip plate and, disposed along a periphery of the tip plate, a rail. The rail includes a microchannel connected to a coolant source.
摘要翻译： 描述了一种在燃气涡轮发动机中使用的涡轮转子叶片，其包括在外径向边缘处具有尖端的翼型件。 翼型件包括压力侧壁和抽吸侧壁，该侧壁在翼型的前缘和后缘处连接在一起，压力侧壁和吸力侧壁从根部延伸到尖端。 尖端包括尖端板，并且沿着尖端板的周边布置有轨道。 导轨包括连接到冷却剂源的微通道。
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公开(公告)号：US08434999B2
公开(公告)日：2013-05-07
申请号：US12731186
申请日：2010-03-25
IPC分类号： F01D11/00
CPC分类号： F16J15/0887 , F01D11/005 , F05D2300/50212
摘要： A spline seal for a hot gas path component is provided. The spline seal may include a first metal layer and a second metal layer. The first metal layer may have a first volumetric thermal expansion coefficient. The second metal layer may be disposed adjacent the first metal layer and have a second volumetric thermal expansion coefficient. The second volumetric thermal expansion coefficient may be higher than the first volumetric thermal expansion coefficient. When the spline seal is exposed to a heat source, the first and second metal layers may deform to provide a seal between the hot gas path component and an adjacent hot gas path component.
摘要翻译： 提供了用于热气路径部件的花键密封。 花键密封件可以包括第一金属层和第二金属层。 第一金属层可以具有第一体积热膨胀系数。 第二金属层可以邻近第一金属层设置并具有第二体积热膨胀系数。 第二体积热膨胀系数可以高于第一体积热膨胀系数。 当花键密封件暴露于热源时，第一和第二金属层可以变形以在热气体路径部件和相邻的热气体通道部件之间提供密封。
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