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公开(公告)号：US08794640B2
公开(公告)日：2014-08-05
申请号：US12731285
申请日：2010-03-25
CPC分类号： F01D11/005 , F01D9/042 , F05D2240/57
摘要： A sealing system for sealing a gap between a first body and a second body includes a first seal having a first portion adapted to be attached to the first body and a second portion extending into the gap. The sealing system also includes a second seal. The second seal has a first portion adapted to be attached to the second body and a second portion extending across the gap. The second portion of the first seal and the second portion of the second seal are adjacent and overlapping with each other to seal the gap.
摘要翻译： 用于密封第一主体和第二主体之间的间隙的密封系统包括具有适于附接到第一主体的第一部分和延伸到间隙中的第二部分的第一密封件。 密封系统还包括第二密封件。 第二密封件具有适于附接到第二主体的第一部分和跨越间隙延伸的第二部分。 第一密封件的第二部分和第二密封件的第二部分相邻并且彼此重叠以密封间隙。
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公开(公告)号：US20110233876A1
公开(公告)日：2011-09-29
申请号：US12731285
申请日：2010-03-25
CPC分类号： F01D11/005 , F01D9/042 , F05D2240/57
摘要： A sealing system for sealing a gap between a first body and a second body includes a first seal having a first portion adapted to be attached to the first body and a second portion extending into the gap. The sealing system also includes a second seal. The second seal has a first portion adapted to be attached to the second body and a second portion extending across the gap. The second portion of the first seal and the second portion of the second seal are adjacent and overlapping with each other to seal the gap.
摘要翻译： 用于密封第一主体和第二主体之间的间隙的密封系统包括具有适于附接到第一主体的第一部分和延伸到间隙中的第二部分的第一密封件。 密封系统还包括第二密封件。 第二密封件具有适于附接到第二主体的第一部分和跨越间隙延伸的第二部分。 第一密封件的第二部分和第二密封件的第二部分相邻并且彼此重叠以密封间隙。
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公开(公告)号：US20140000285A1
公开(公告)日：2014-01-02
申请号：US13539842
申请日：2012-07-02
CPC分类号： F01D9/02 , B22C9/04 , B22C9/10 , F01D5/187 , F01D9/041 , F01D25/12 , F05D2230/21 , F05D2230/211 , F05D2240/81 , F05D2250/185 , F05D2260/2214 , Y02T50/672 , Y02T50/676
摘要： A turbine vane for a gas turbine engine includes inner and outer platforms joined by a radially extending airfoil. The airfoil includes leading and trailing edges joined by spaced apart pressure and suction sides to provide an exterior airfoil surface. The airfoil includes an airfoil cooling passage. A platform cooling passage is arranged within at least one of the inner and outer platforms. The platform cooling passage includes multiple cooling regions with one of the cooling regions arranged beneath the airfoil cooling passage.
摘要翻译： 用于燃气涡轮发动机的涡轮叶片包括通过径向延伸的翼型件连接的内平台和外平台。 翼型件包括通过间隔开的压力和吸力侧连接的前缘和后缘，以提供外部翼面表面。 翼型件包括翼型件冷却通道。 平台冷却通道布置在内平台和外平台中的至少一个中。 平台冷却通道包括多个冷却区域，其中一个冷却区域布置在翼型冷却通道下方。
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公开(公告)号：US09021816B2
公开(公告)日：2015-05-05
申请号：US13539842
申请日：2012-07-02
CPC分类号： F01D9/02 , B22C9/04 , B22C9/10 , F01D5/187 , F01D9/041 , F01D25/12 , F05D2230/21 , F05D2230/211 , F05D2240/81 , F05D2250/185 , F05D2260/2214 , Y02T50/672 , Y02T50/676
摘要： A turbine vane for a gas turbine engine includes inner and outer platforms joined by a radially extending airfoil. The airfoil includes leading and trailing edges joined by spaced apart pressure and suction sides to provide an exterior airfoil surface. The airfoil includes an airfoil cooling passage. A platform cooling passage is arranged within at least one of the inner and outer platforms. The platform cooling passage includes multiple cooling regions with one of the cooling regions arranged beneath the airfoil cooling passage.
摘要翻译： 用于燃气涡轮发动机的涡轮叶片包括通过径向延伸的翼型件连接的内平台和外平台。 翼型件包括通过间隔开的压力和吸力侧连接的前缘和后缘，以提供外部翼面表面。 翼型件包括翼型件冷却通道。 平台冷却通道布置在内平台和外平台中的至少一个中。 平台冷却通道包括多个冷却区域，其中一个冷却区域布置在翼型冷却通道下方。
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公开(公告)号：US08360716B2
公开(公告)日：2013-01-29
申请号：US12730180
申请日：2010-03-23
申请人： Russell J. Bergman , Stephen J. Yea , Leonard A. Bach , Joseph W. Bridges, Jr. , Lawrence J. Willey , Brandon W. Spangler
发明人： Russell J. Bergman , Stephen J. Yea , Leonard A. Bach , Joseph W. Bridges, Jr. , Lawrence J. Willey , Brandon W. Spangler
IPC分类号： F01D9/00
CPC分类号： F01D9/02 , F01D11/005 , F05D2240/128 , F05D2240/80 , Y02T50/671
摘要： A nozzle segment for a gas turbine engine includes a flange which extends from a vane platform, the flange includes a hollow cavity.
摘要翻译： 用于燃气涡轮发动机的喷嘴段包括从叶片平台延伸的凸缘，所述凸缘包括中空腔。
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公开(公告)号：US20110236199A1
公开(公告)日：2011-09-29
申请号：US12730180
申请日：2010-03-23
申请人： Russell J. Bergman , Stephen J. Yee , Leonard A. Bach , Joseph W. Bridges, JR. , Lawrence J. Willey , Brandon W. Spangler
发明人： Russell J. Bergman , Stephen J. Yee , Leonard A. Bach , Joseph W. Bridges, JR. , Lawrence J. Willey , Brandon W. Spangler
IPC分类号： F01D9/02
CPC分类号： F01D9/02 , F01D11/005 , F05D2240/128 , F05D2240/80 , Y02T50/671
摘要： A nozzle segment for a gas turbine engine includes a flange which extends from a vane platform, the flange includes a hollow cavity.
摘要翻译： 用于燃气涡轮发动机的喷嘴段包括从叶片平台延伸的凸缘，所述凸缘包括中空腔。
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公开(公告)号：US20140000287A1
公开(公告)日：2014-01-02
申请号：US13539917
申请日：2012-07-02
IPC分类号： F01D25/12
CPC分类号： F01D25/12 , F01D9/02 , F01D9/041 , F05D2240/81 , F05D2250/74 , F05D2260/202 , Y02T50/672 , Y02T50/673 , Y02T50/676
摘要： A turbine vane for a gas turbine engine includes inner and outer platforms joined by a radially extending airfoil. The airfoil includes leading and trailing edges joined by spaced apart pressure and suction sides to provide an exterior airfoil surface. The inner and outer platforms respectively include inner and outer sets of film cooling holes, wherein one of the inner and outer sets of film cooling holes are formed in substantial conformance with platform cooling hole locations described by one of the sets of Cartesian coordinates set forth in Tables 1 and 2. The Cartesian coordinates are provided by an axial coordinate, a circumferential coordinate, and a radial coordinate, relative to a zero-coordinate. The cooling holes with Cartesian coordinates in Tables 1 and 2 have a diametrical surface tolerance relative to the specified coordinates of 0.200 inches (5.08 mm).
摘要翻译： 用于燃气涡轮发动机的涡轮叶片包括通过径向延伸的翼型件连接的内平台和外平台。 翼型件包括通过间隔开的压力和吸力侧连接的前缘和后缘，以提供外部翼面表面。 内部和外部平台分别包括内部和外部薄膜冷却孔组，其中内部和外部薄膜冷却孔组中的一个基本上与基于以下的笛卡尔坐标系中的一组所描述的平台冷却孔位置形成： 表1和2.相对于零坐标，笛卡尔坐标由轴向坐标，圆周坐标和径向坐标提供。 表1和表2中笛卡尔坐标的冷却孔相对于0.200英寸（5.08毫米）的指定坐标具有直径表面公差。
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公开(公告)号：US09222364B2
公开(公告)日：2015-12-29
申请号：US13586110
申请日：2012-08-15
申请人： Michael Leslie Clyde Papple , Russell J. Bergman , Mohammed Ennacer , Shawn J. Gregg , Dominic J. Mongillo
发明人： Michael Leslie Clyde Papple , Russell J. Bergman , Mohammed Ennacer , Shawn J. Gregg , Dominic J. Mongillo
CPC分类号： F01D9/041 , F01D5/187 , F01D9/023 , F01D25/12 , F05D2220/32 , F05D2240/12 , F05D2240/81 , F05D2250/185 , F05D2260/201 , F05D2260/22141 , Y02T50/676
摘要： A component for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a platform having a first path side and a second path side and a platform cooling circuit disposed on one of the first path side and the second path side of the platform. The platform cooling circuit includes a first core cavity, a cavity in fluid communication with the first core cavity, and a cover plate positioned to cover at least the cavity.
摘要翻译： 根据本公开的示例性方面的用于燃气涡轮发动机的部件尤其包括具有第一路径侧和第二路径侧的平台以及设置在第一路径侧和第二路径侧中的一个上的平台冷却回路 平台的路径一侧。 平台冷却回路包括第一芯腔，与第一芯腔流体连通的空腔，以及定位成覆盖至少空腔的盖板。
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公开(公告)号：US20140047843A1
公开(公告)日：2014-02-20
申请号：US13586110
申请日：2012-08-15
申请人： Michael Leslie Clyde Papple , Russell J. Bergman , Mohammed Ennacer , Shawn J. Gregg , Dominic J. Mongillo
发明人： Michael Leslie Clyde Papple , Russell J. Bergman , Mohammed Ennacer , Shawn J. Gregg , Dominic J. Mongillo
CPC分类号： F01D9/041 , F01D5/187 , F01D9/023 , F01D25/12 , F05D2220/32 , F05D2240/12 , F05D2240/81 , F05D2250/185 , F05D2260/201 , F05D2260/22141 , Y02T50/676
摘要： A component for a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a platform having a first path side and a second path side and a platform cooling circuit disposed on one of the first path side and the second path side of the platform. The platform cooling circuit includes a first core cavity, a cavity in fluid communication with the first core cavity, and a cover plate positioned to cover at least the cavity.
摘要翻译： 根据本公开的示例性方面的用于燃气涡轮发动机的部件尤其包括具有第一路径侧和第二路径侧的平台以及设置在第一路径侧和第二路径侧中的一个上的平台冷却回路 平台的路径一侧。 平台冷却回路包括第一芯腔，与第一芯腔流体连通的空腔，以及定位成覆盖至少空腔的盖板。
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公开(公告)号：US20130183145A1
公开(公告)日：2013-07-18
申请号：US13351290
申请日：2012-01-17
IPC分类号： F01D11/00
CPC分类号： F01D11/001 , F01D9/04 , F01D11/025
摘要： A turbine section has a turbine rotor carrying turbine blades. The turbine blades include seal members at a radially inner location. A vane section is formed of a plurality of circumferentially spaced vane components, each of which has an airfoil extending radially outwardly of a platform. A first seal member is fixed to the platform, and is positioned to be adjacent a seal from a blade which is positioned in one axial direction relative to the first seal member. A second seal member extends circumferentially beyond at least a plurality of the vane components and is positioned to be adjacent a seal member of a blade on an opposed axial side from the first blade. A vane component is also disclosed and claimed.
摘要翻译： 涡轮部分具有承载涡轮叶片的涡轮转子。 涡轮机叶片包括在径向内部位置处的密封构件。 叶片部分由多个周向间隔开的叶片部件形成，每个叶片部件具有从平台径向向外延伸的翼型件。 第一密封构件固定到平台上，并且被定位成与相对于第一密封构件沿一个轴向方向定位的叶片相邻的密封件。 第二密封构件周向地延伸超过至少多个叶片部件，并且定位成在与第一叶片相对的轴向侧上与叶片的密封构件相邻。 还公开并要求保护叶片部件。
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