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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：US08651802B2
公开(公告)日：2014-02-18
申请号：US12726021
申请日：2010-03-17
IPC分类号： F03B11/00
CPC分类号： F01D9/041 , F01D25/12 , F05D2260/201 , Y02T50/676 , Y10T428/24273 , Y10T428/24802
摘要： Embodiments of a cover plate and material blank for forming the cover plate may include features and characteristics to accommodate tolerance issues in a turbine vane assembly. In one embodiment, the cover plate is formed from a material blank configured to provide the cover plate with a flexible flange area that can be secured to the turbine vane assembly. The flange area may have a range of motion that may be responsive to an installation force, which effectively modifies the configuration of the cover plate to such degree as to seal the cover plate to the turbine vane assembly.
摘要翻译： 用于形成盖板的盖板和材料坯料的实施例可以包括用于适应涡轮叶片组件中的公差问题的特征和特征。 在一个实施例中，盖板由材料坯料形成，其被配置为向盖板提供可固定到涡轮叶片组件的柔性凸缘区域。 凸缘区域可以具有可以响应于安装力的运动范围，该安装力有效地将盖板的构造改变为将盖板密封到涡轮叶片组件的程度。
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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：US20110206501A1
公开(公告)日：2011-08-25
申请号：US12711327
申请日：2010-02-24
CPC分类号： F01D11/005 , F01D9/041 , F01D25/12 , F05D2220/323 , F05D2230/12 , F05D2230/21 , F05D2240/12 , F05D2240/55 , F05D2250/75 , F05D2260/20
摘要： A segmented engine component has multiple segments which are connected to each other via a featherseal arrangement. Each of the components has a combined featherseal slot and lightening pocket.
摘要翻译： 分段发动机部件具有多个段，它们通过羽密排列相互连接。 每个组件具有组合的羽状槽和减轻口袋。
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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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公开(公告)号：US20110229305A1
公开(公告)日：2011-09-22
申请号：US12726021
申请日：2010-03-17
CPC分类号： F01D9/041 , F01D25/12 , F05D2260/201 , Y02T50/676 , Y10T428/24273 , Y10T428/24802
摘要： Embodiments of a cover plate and material blank for forming the cover plate may include features and characteristics to accommodate tolerance issues in a turbine vane assembly. In one embodiment, the cover plate is formed from a material blank configured to provide the cover plate with a flexible flange area that can be secured to the turbine vane assembly. The flange area may have a range of motion that may be responsive to an installation force, which effectively modifies the configuration of the cover plate to such degree as to seal the cover plate to the turbine vane assembly.
摘要翻译： 用于形成盖板的盖板和材料坯料的实施例可以包括用于适应涡轮叶片组件中的公差问题的特征和特征。 在一个实施例中，盖板由材料坯料形成，其被配置为向盖板提供可固定到涡轮叶片组件的柔性凸缘区域。 凸缘区域可以具有可以响应于安装力的运动范围，该安装力有效地将盖板的构造改变为将盖板密封到涡轮叶片组件的程度。
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