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公开(公告)号：US09109453B2
公开(公告)日：2015-08-18
申请号：US13585982
申请日：2012-08-15
CPC分类号： F01D5/186 , F01D9/041 , F02C7/18 , F05D2240/121 , F05D2250/74 , F05D2260/202 , Y02T50/673 , Y02T50/676
摘要： An airfoil includes a leading edge, a trailing edge, a pressure side surface extending from the leading edge to the trailing edge, a suction side surface extending from the leading edge to the trailing edge and generally opposite the pressure side surface and a plurality of cooling holes. The cooling holes are positioned on the airfoil in accordance with X, Y and Z Cartesian coordinate values set forth in an accompanying Table.
摘要翻译： 机翼包括前缘，后缘，从前缘延伸到后缘的压力侧表面，从前缘延伸到后缘并且大致相对于压力侧表面的吸力侧表面和多个冷却 孔。 冷却孔根据附表中列出的X，Y和Z笛卡尔坐标值定位在翼型上。
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公开(公告)号：US20150192021A1
公开(公告)日：2015-07-09
申请号：US13585982
申请日：2012-08-15
CPC分类号： F01D5/186 , F01D9/041 , F02C7/18 , F05D2240/121 , F05D2250/74 , F05D2260/202 , Y02T50/673 , Y02T50/676
摘要： An airfoil includes a leading edge, a trailing edge, a pressure side surface extending from the leading edge to the trailing edge, a suction side surface extending from the leading edge to the trailing edge and generally opposite the pressure side surface and a plurality of cooling holes. The cooling holes are positioned on the airfoil in accordance with X, Y and Z Cartesian coordinate values set forth in an accompanying Table.
摘要翻译： 机翼包括前缘，后缘，从前缘延伸到后缘的压力侧表面，从前缘延伸到后缘并且大致相对于压力侧表面的吸力侧表面和多个冷却 孔。 冷却孔根据附表中列出的X，Y和Z笛卡尔坐标值定位在翼型上。
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公开(公告)号：US08961108B2
公开(公告)日：2015-02-24
申请号：US13439277
申请日：2012-04-04
申请人： Russell J. Bergman , Shawn J. Gregg , Michael Papple , Paul M. Lutjen , Joseph T. Caprario , Mohammed Ennacer , Thurman Carlo Dabbs
发明人： Russell J. Bergman , Shawn J. Gregg , Michael Papple , Paul M. Lutjen , Joseph T. Caprario , Mohammed Ennacer , Thurman Carlo Dabbs
IPC分类号： F01D9/06
CPC分类号： F01D25/246 , F01D25/14 , F05D2240/81
摘要： A cooling system for a gas turbine engine includes a first plenum, a first cooling flow passageway, and a second cooling flow passageway. The first cooling flow passageway is in fluid communication with the first plenum and with a first airfoil cooling channel within an airfoil of the stator vane. The first airfoil cooling channel is for cooling a leading edge of the airfoil. The second cooling flow passageway is in fluid communication with the first plenum and with a platform cooling channel within an outer diameter platform of the stator vane. The first cooling flow passageway and the second cooling flow passageway are disposed within a mounting hook. The first cooling flow passageway and the second cooling flow passageway are not in fluid communication with each other.
摘要翻译： 用于燃气涡轮发动机的冷却系统包括第一增压室，第一冷却流通道和第二冷却流通道。 第一冷却流通道与第一集气室流体连通，并且在定子叶片的翼型内具有第一翼型冷却通道。 第一翼型冷却通道用于冷却翼型件的前缘。 第二冷却流通道与第一集气室流体连通，并且在定子叶片的外径平台内具有平台冷却通道。 第一冷却流通道和第二冷却流通道设置在安装钩内。 第一冷却流路和第二冷却流路不相互流体连通。
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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：US20140000286A1
公开(公告)日：2014-01-02
申请号：US13539873
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. 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。 内平台和外平台分别包括内套和外套薄膜冷却孔。 内外套膜冷却孔中的一个基本上符合由表1和表2中所示的笛卡尔坐标系中的一组描述的平台冷却孔位置。笛卡尔坐标由轴向坐标，圆周方向 坐标和径向坐标，相对于零坐标。 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：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：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：US20140060084A1
公开(公告)日：2014-03-06
申请号：US13599226
申请日：2012-08-30
申请人： Shawn J. GREGG , Dominic J. MONGILLO , Michael Leslie Clyde PAPPLE , Russell J. BERGMAN , Mohammed ENNACER
发明人： Shawn J. GREGG , Dominic J. MONGILLO , Michael Leslie Clyde PAPPLE , Russell J. BERGMAN , Mohammed ENNACER
IPC分类号： F01D5/18
CPC分类号： F01D5/188 , F01D5/187 , F01D5/189 , F01D9/041 , F01D25/12 , F02C7/12 , F04D29/324 , F04D29/542 , F04D29/582 , F05D2220/32 , F05D2240/126 , F05D2240/30 , F05D2260/201 , F05D2260/2212 , F05D2260/22141 , Y02T50/676
摘要： A component for a gas turbine engine according to an exemplary aspect of the present disclosure including, among other things, an airfoil that extends between a leading edge and a trailing edge and a cooling circuit disposed inside of the airfoil. The cooling circuit includes at least one core cavity that extends inside of the airfoil, a baffle received within the at least one core cavity, a plurality of pedestals positioned adjacent to the at least one core cavity and a first plurality of axial ribs positioned between the plurality of pedestals and the trailing edge of the airfoil.
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，其特征在于，包括在前缘和后缘之间延伸的翼型件和设置在翼型内部的冷却回路。 所述冷却回路包括至少一个在所述翼型件内部延伸的芯腔，容纳在所述至少一个芯腔内的挡板，与所述至少一个芯腔相邻定位的多个基座和位于所述至少一个芯腔之间的第一多个轴向肋 多个基座和翼型件的后缘。
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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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