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1. 发明授权

US07726944B2 Turbine blade with improved durability tip cap 有权
标题翻译：涡轮叶片具有改进的耐久性顶盖
公开(公告)号：US07726944B2
公开(公告)日：2010-06-01
申请号：US11524102
申请日：2006-09-20
申请人： Richard H. Page , Wieslaw A. Chlus
发明人： Richard H. Page , Wieslaw A. Chlus
IPC分类号： F01D5/18
CPC分类号： F01D5/20 , F05D2240/307 , F05D2260/20 , F05D2260/2214 , Y02T50/676
摘要： A gas turbine engine has a turbine blade having a tip cap to close off internal cooling passages. The tip cap is formed with a plurality of purge holes, with there being at least two rows of purge holes. The increased number of purge holes spreads the cooling air outwardly across more of the surface area of the tip cap, and provides the tip cap with a better ability to withstand the extreme temperatures it faces in use.
摘要翻译：燃气涡轮发动机具有涡轮叶片，其具有尖端盖以封闭内部冷却通道。尖端盖形成有多个吹扫孔，其中至少有两排吹扫孔。吹扫孔数量的增加将冷却空气向外扩散到尖端盖的更多表面区域，并且提供顶盖具有更好的耐受其使用的极端温度的能力。

2. 发明申请

US20100080711A1 TURBINE BLADE WITH IMPROVED DURABILITY TIP CAP 有权
标题翻译：涡轮叶片具有改进的耐久性提示
公开(公告)号：US20100080711A1
公开(公告)日：2010-04-01
申请号：US11524102
申请日：2006-09-20
申请人： Richard H. Page , Wieslaw A. Chlus
发明人： Richard H. Page , Wieslaw A. Chlus
IPC分类号： F01D5/18
CPC分类号： F01D5/20 , F05D2240/307 , F05D2260/20 , F05D2260/2214 , Y02T50/676
摘要： A gas turbine engine has a turbine blade having a tip cap to close off internal cooling passages. The tip cap is formed with a plurality of purge holes, with there being at least two rows of purge holes. The increased number of purge holes spreads the cooling air outwardly across more of the surface area of the tip cap, and provides the tip cap with a better ability to withstand the extreme temperatures it faces in use.
摘要翻译：燃气涡轮发动机具有涡轮叶片，其具有尖端盖以封闭内部冷却通道。尖端盖形成有多个吹扫孔，其中至少有两排吹扫孔。吹扫孔数量的增加将冷却空气向外扩散到尖端盖的更多表面区域，并且提供顶盖具有更好的耐受其使用的极端温度的能力。

3. 发明申请

US20100122789A1 Investment Casting Cores and Methods 有权
标题翻译：投资铸造芯和方法
公开(公告)号：US20100122789A1
公开(公告)日：2010-05-20
申请号：US12271980
申请日：2008-11-17
申请人： Justin D. Piggush , Karl A. Mentz , Richard H. Page , Jesse R. Christophel , Ricardo Trindade
发明人： Justin D. Piggush , Karl A. Mentz , Richard H. Page , Jesse R. Christophel , Ricardo Trindade
IPC分类号： B22C9/00 , B22C9/10 , B22C7/00
CPC分类号： B22C7/02 , B22C9/04 , B22C9/103
摘要： An investment casting core combination includes a metallic casting core and a ceramic feedcore. A first region of the metallic casting core is embedded in the ceramic feedcore. A mating edge portion of the metallic casting core includes a number of projections. The first region is along at least some of the projections. A number of recesses span gaps between adjacent projections. The ceramic feedcore includes a number of compartments respectively receiving the metallic casting core projections. The ceramic feedcore further includes a number of portions between the compartments and respectively received in the metallic casting core recesses.
摘要翻译：熔模铸造核心组合包括金属铸造芯和陶瓷馈线。金属铸造芯的第一区域嵌入在陶瓷原料中。金属铸造芯的配合边缘部分包括多个突起。第一个区域至少是一些预测。多个凹槽跨越相邻突起之间的间隙。陶瓷馈线包括分别容纳金属铸造芯凸起的多个隔室。陶瓷进料还包括隔室之间的多个部分，并且分别容纳在金属铸造芯凹部中。

4. 发明授权

US07713027B2 Turbine blade with split impingement rib 有权
标题翻译：涡轮叶片带有分体冲击肋
公开(公告)号：US07713027B2
公开(公告)日：2010-05-11
申请号：US11511114
申请日：2006-08-28
申请人： Anthony P. Cherolis , Richard H. Page
发明人： Anthony P. Cherolis , Richard H. Page
IPC分类号： F01D5/18
CPC分类号： F01D5/187 , F05D2260/201 , F05D2260/22141 , Y02T50/676
摘要： A gas turbine engine is provided with an airfoil component that is disclosed as a turbine blade. Internal cooling passages circulate air within the blade. An impingement rib separates a cooling air channel from a pedestal array, and includes cross-over holes to meter the flow of air into the pedestal array. A lower end of the impingement rib is split to reduce stress concentrations between the impingement rib and a platform. Further, the pedestals adjacent to the lower end of the impingement rib are formed to be stubs, which do not extend entirely across a width of the blade. The disclosed structure reduces the stress concentration at an area where the impingement rib meets the platform.
摘要翻译：燃气涡轮发动机设置有被公开为涡轮叶片的翼型件。内部冷却通道使叶片内的空气循环。冲击肋将冷却空气通道与基座阵列分开，并且包括用于计量进入基座阵列的空气流的交叉孔。冲击肋的下端被分裂以减少冲击肋和平台之间的应力集中。此外，与撞击肋的下端相邻的基座形成为不完全延伸穿过叶片的宽度的短截线。所公开的结构降低了冲击肋与平台相遇的区域处的应力集中。

5. 发明申请

US20090208339A1 BLADE ROOT STRESS RELIEF 审中-公开
标题翻译：叶片根部紧张
公开(公告)号：US20090208339A1
公开(公告)日：2009-08-20
申请号：US12032231
申请日：2008-02-15
申请人： Anthony P. Cherolis , Richard H. Page , Karl A. Mentz
发明人： Anthony P. Cherolis , Richard H. Page , Karl A. Mentz
IPC分类号： F01D5/30 , B21K25/00 , B23P6/00
CPC分类号： F01D5/3007 , Y10T29/4932 , Y10T29/49321
摘要： In a gas turbine engine, a stress relief is formed along a blade root and disk slot junction. An exemplary relief is a chamfer along the pressure side of the blade root extending forward from the aft face of the root.
摘要翻译：在燃气涡轮发动机中，沿叶片根部和盘槽结合部形成应力消除。示例性的浮雕是沿着从根部的后面向前延伸的叶片根部的压力侧的倒角。

6. 发明授权

US08100165B2 Investment casting cores and methods 有权
标题翻译：投资核心和方法
公开(公告)号：US08100165B2
公开(公告)日：2012-01-24
申请号：US12271980
申请日：2008-11-17
申请人： Justin D. Piggush , Karl A. Mentz , Richard H. Page , Jesse R. Christophel , Ricardo Trindade
发明人： Justin D. Piggush , Karl A. Mentz , Richard H. Page , Jesse R. Christophel , Ricardo Trindade
IPC分类号： B22C9/10 , B22C9/04 , B22C7/00
CPC分类号： B22C7/02 , B22C9/04 , B22C9/103
摘要： An investment casting core combination includes a metallic casting core and a ceramic feedcore. A first region of the metallic casting core is embedded in the ceramic feedcore. A mating edge portion of the metallic casting core includes a number of projections. The first region is along at least some of the projections. A number of recesses span gaps between adjacent projections. The ceramic feedcore includes a number of compartments respectively receiving the metallic casting core projections. The ceramic feedcore further includes a number of portions between the compartments and respectively received in the metallic casting core recesses.
摘要翻译：熔模铸造核心组合包括金属铸造芯和陶瓷馈线。金属铸造芯的第一区域嵌入在陶瓷原料中。金属铸造芯的配合边缘部分包括多个突起。第一个区域至少是一些预测。多个凹槽跨越相邻突起之间的间隙。陶瓷馈线包括分别容纳金属铸造芯凸起的多个隔室。陶瓷进料还包括隔室之间的多个部分，并且分别容纳在金属铸造芯凹部中。

7. 发明授权

US08347947B2 Process and refractory metal core for creating varying thickness microcircuits for turbine engine components 有权
$Process and refractory metal core for creating varying thickness microcircuits for turbine engine components$
公开(公告)号：US08347947B2
公开(公告)日：2013-01-08
申请号：US12372181
申请日：2009-02-17
申请人： Bryan P. Dube , Ryan Shepard Levy , Richard H. Page
发明人： Bryan P. Dube , Ryan Shepard Levy , Richard H. Page
IPC分类号： B22C9/10 , B28B7/28
CPC分类号： B22C9/10 , B22C9/04 , B22C9/108 , B22D29/001 , F01D5/187 , F05D2230/00 , F05D2230/21 , F05D2240/121 , F05D2240/122 , F05D2240/303 , F05D2240/304 , F05D2250/185 , F05D2300/13
摘要： The present disclosure is directed to a refractory metal core for use in forming varying thickness microcircuits in turbine engine components, a process for forming the refractory metal core, and a process for forming the turbine engine components. The refractory metal core is used in the casting of a turbine engine component. The core is formed by a sheet of refractory metal material having a curved trailing edge portion integrally formed with a leading edge portion.

8. 发明申请

US20080050244A1 Turbine blade with split impingement rib 有权
标题翻译：涡轮叶片带有分体冲击肋
公开(公告)号：US20080050244A1
公开(公告)日：2008-02-28
申请号：US11511114
申请日：2006-08-28
申请人： Anthony P. Cherolis , Richard H. Page
发明人： Anthony P. Cherolis , Richard H. Page
IPC分类号： F01D5/18
CPC分类号： F01D5/187 , F05D2260/201 , F05D2260/22141 , Y02T50/676
摘要： A gas turbine engine is provided with an airfoil component that is disclosed as a turbine blade. Internal cooling passages circulate air within the blade. An impingement rib separates a cooling air channel from a pedestal array, and includes cross-over holes to meter the flow of air into the pedestal array. A lower end of the impingement rib is split to reduce stress concentrations between the impingement rib and a platform. Further, the pedestals adjacent to the lower end of the impingement rib are formed to be stubs, which do not extend entirely across a width of the blade. The disclosed structure reduces the stress concentration at an area where the impingement rib meets the platform.
摘要翻译：燃气涡轮发动机设置有被公开为涡轮叶片的翼型件。内部冷却通道使叶片内的空气循环。冲击肋将冷却空气通道与基座阵列分开，并且包括用于计量进入基座阵列的空气流的交叉孔。冲击肋的下端被分裂以减少冲击肋和平台之间的应力集中。此外，与撞击肋的下端相邻的基座形成为不完全延伸穿过叶片的宽度的短截线。所公开的结构降低了冲击肋与平台相遇的区域处的应力集中。

9. 发明授权

US07273353B2 Shroud honeycomb cutter 有权
公开(公告)号：US07273353B2
公开(公告)日：2007-09-25
申请号：US11503779
申请日：2006-08-14
申请人： Bryan P. Dube , Richard H. Page
发明人： Bryan P. Dube , Richard H. Page
IPC分类号： F01D11/12
CPC分类号： F01D11/127 , F01D5/225 , F05B2240/33
摘要： A turbine blade for use in a gas turbine engine is provided. The turbine blade includes an airfoil portion having a tip end, a shroud attached to the tip end, which shroud has an outer surface, and a knife edge attached to an outer surface of the shroud. The knife edge has a pair of cutter blades disposed substantially over an axis of the airfoil portion.

10. 发明申请

US20100206512A1 Process and Refractory Metal Core For Creating Varying Thickness Microcircuits For Turbine Engine Components 有权
$Process and Refractory Metal Core For Creating Varying Thickness Microcircuits For Turbine Engine Components$
标题翻译：用于创建涡轮发动机部件的不同厚度微电路的工艺和耐火金属芯
公开(公告)号：US20100206512A1
公开(公告)日：2010-08-19
申请号：US12372181
申请日：2009-02-17
申请人： Bryan P. Dube , Ryan Shepard Levy , Richard H. Page
发明人： Bryan P. Dube , Ryan Shepard Levy , Richard H. Page
IPC分类号： B22D29/00 , B22C9/10
CPC分类号： B22C9/10 , B22C9/04 , B22C9/108 , B22D29/001 , F01D5/187 , F05D2230/00 , F05D2230/21 , F05D2240/121 , F05D2240/122 , F05D2240/303 , F05D2240/304 , F05D2250/185 , F05D2300/13
摘要： The present disclosure is directed to a refractory metal core for use in forming varying thickness microcircuits in turbine engine components, a process for forming the refractory metal core, and a process for forming the turbine engine components. The refractory metal core is used in the casting of a turbine engine component. The core is formed by a sheet of refractory metal material having a curved trailing edge portion integrally formed with a leading edge portion.
摘要翻译：本公开涉及用于在涡轮发动机部件中形成变化的厚度微电路的难熔金属芯，用于形成耐火金属芯的方法以及用于形成涡轮发动机部件的工艺。耐火金属芯用于涡轮发动机部件的铸造。芯由具有与前缘部一体形成的弯曲后缘部的耐火金属材料片形成。

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