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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：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：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：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：US20120171045A1
公开(公告)日：2012-07-05
申请号：US12983635
申请日：2011-01-03
CPC分类号： B05B12/24 , B05C1/02 , B05C3/09 , B05C5/00 , Y10T29/49229
摘要： A system comprises a turbine component and a fixture. The turbine component comprises a first end, a second end, a first region with a first feature and a second region with a second feature. The fixture comprises first and second end blocks adjacent the first and second ends of the turbine component, and a load beam coupling the first and second end blocks to retain the turbine component therebetween. A compliant mask is positioned against the turbine component, covering the first region and leaving the second region uncovered. A removable coating is applied to the turbine component, coating the second feature and leaving the first feature uncoated.
摘要翻译： 一种系统包括涡轮机部件和固定装置。 涡轮机部件包括第一端，第二端，具有第一特征的第一区域和具有第二特征的第二区域。 固定装置包括与涡轮机部件的第一和第二端相邻的第一和第二端块，以及联接第一和第二端部块以将涡轮机部件保持在其间的负载梁。 适应性掩模抵靠涡轮机部件定位，覆盖第一区域并使第二区域未被覆盖。 将可移除的涂层施加到涡轮机部件上，涂覆第二特征并使第一特征未被涂覆。
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公开(公告)号：US09322279B2
公开(公告)日：2016-04-26
申请号：US13539838
申请日：2012-07-02
CPC分类号： F01D5/186 , F01D9/065 , Y02T50/676
摘要： An airfoil according to an exemplary embodiment of the present disclosure can include an airfoil body having a plurality of film cooling holes that extend through an exterior surface of the airfoil body. Each of the plurality of film cooling holes break through the exterior surface at geometric coordinates in accordance with Cartesian coordinate values of X, Y and Z as set forth in Table 1. Each of the geometric coordinates is measured from a reference point on a leading edge rail of a platform of the airfoil.
摘要翻译： 根据本公开的示例性实施例的翼型件可以包括具有延伸穿过翼型件主体的外表面的多个膜冷却孔的翼型件主体。 多个膜冷却孔中的每一个根据如表1所示的X，Y和Z的笛卡尔坐标值以几何坐标突破外表面。每个几何坐标是从前缘上的参考点 机翼平台的轨道。
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公开(公告)号：US09115597B2
公开(公告)日：2015-08-25
申请号：US13539917
申请日：2012-07-02
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：US08707712B2
公开(公告)日：2014-04-29
申请号：US13539873
申请日：2012-07-02
IPC分类号： F02C7/12
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：US20140000283A1
公开(公告)日：2014-01-02
申请号：US13539806
申请日：2012-07-02
CPC分类号： F01D5/18 , F01D5/187 , F01D9/02 , F01D25/12 , F02C3/04 , F04D29/324 , F04D29/542 , F04D29/582 , F05D2220/32 , F05D2240/35 , F05D2240/81 , F05D2250/11 , F05D2260/201 , F05D2260/22141
摘要： A component for a gas turbine engine according to an exemplary embodiment of the present disclosure includes, among other possible things, a platform having a non-gas path side and a gas path side, an airfoil extending from the gas path side of the platform, and a cover plate positioned adjacent to the non-gas path side of the platform. The cover plate can include a first plurality of openings that communicate a first portion of a cooling air to a first cooling cavity of the platform and a second plurality of openings that can communicate a second portion of the cooling air to the second cooling cavity that is separate from the first cooling cavity. Each of the first cooling cavity and the second cooling cavity can include a plurality of augmentation features.
摘要翻译： 根据本公开的示例性实施例的用于燃气涡轮发动机的部件除了其它可能的内容之外还包括具有非气体通路侧和气体通路侧的平台，从平台的气体路径侧延伸的翼型， 以及邻近所述平台的非气体路径侧定位的盖板。 盖板可以包括将冷却空气的第一部分连通到平台的第一冷却腔的第一多个开口以及可将冷却空气的第二部分连通到第二冷却腔的第二多个开口， 与第一个冷却腔分开。 第一冷却腔和第二冷却腔中的每一个可以包括多个增强特征。
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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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