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1. 发明申请

US20110142684A1 Turbine Engine Airfoil and Platform Assembly 有权
标题翻译：涡轮发动机翼型和平台组件
公开(公告)号：US20110142684A1
公开(公告)日：2011-06-16
申请号：US12638034
申请日：2009-12-15
申请人： Christian X. Campbell , Allister W. James , Jay A. Morrison
发明人： Christian X. Campbell , Allister W. James , Jay A. Morrison
IPC分类号： F01D5/30 , B23P15/04
CPC分类号： B23P15/04 , F01D5/081 , F01D5/147 , F01D5/3007 , F01D11/008 , F05D2230/51 , F05D2230/52 , F05D2240/40 , F05D2260/36 , Y10T29/49337
摘要： A turbine airfoil (22A) is formed by a first process using a first material. A platform (30A) is formed by a second process using a second material that may be different from the first material. The platform (30A) is assembled around a shank (23A) of the airfoil. One or more pins (36A) extend from the platform into holes (28) in the shank (23A). The platform may be formed in two portions (32A, 34A) and placed around the shank, enclosing it. The two platform portions may be bonded to each other. Alternately, the platform (30B) may be cast around the shank (23B) using a metal alloy with better castability than that of the blade and shank, which may be specialized for thermal tolerance. The pins (36A-36D) or holes for them do not extend to an outer surface (31) of the platform, avoiding stress concentrations.
摘要翻译：涡轮机翼片（22A）通过使用第一材料的第一工艺形成。使用可能不同于第一材料的第二材料的第二工艺形成平台（30A）。平台（30A）组装在机翼的柄（23A）周围。一个或多个销（36A）从平台延伸到柄（23A）中的孔（28）中。平台可以形成为两部分（32A，34A）并且围绕柄部放置并包围该平台。两个平台部分可以彼此结合。或者，平台（30B）可以使用具有比刀片和柄部更好的铸造性的金属合金围绕杆（23B）铸造，其可以专用于耐热性。销（36A-36D）或它们的孔不延伸到平台的外表面（31），以避免应力集中。

2. 发明授权

US08714920B2 Turbine airfoil to shround attachment 失效
标题翻译：涡轮机翼以遮蔽附件
公开(公告)号：US08714920B2
公开(公告)日：2014-05-06
申请号：US12752460
申请日：2010-04-01
申请人： Christian X. Campbell , Jay A. Morrison , Allister W. James , Raymond G. Snider , Daniel M. Eshak , John J. Marra , Brian J. Wessell
发明人： Christian X. Campbell , Jay A. Morrison , Allister W. James , Raymond G. Snider , Daniel M. Eshak , John J. Marra , Brian J. Wessell
IPC分类号： F01D1/02 , F04D29/54
CPC分类号： F01D11/005 , B22D19/00 , B22D19/0081 , F01D9/044 , F05D2230/21 , F05D2240/80
摘要： A turbine airfoil (31) with an end portion (42) that tapers (44) toward the end (43) of the airfoil. A ridge (46) extends around the end portion. It has proximal (66) and distal (67) sides. A shroud platform (50) is bi-cast onto the end portion around the ridge without bonding. Cooling shrinks the platform into compression (62) on the end portion (42) of the airfoil. Gaps between the airfoil and platform are formed using a fugitive material (56) in the bi-casting stage. These gaps are designed in combination with the taper angle (44) to accommodate differential thermal expansion while maintaining a gas seal along the contact surfaces. The taper angle (44) may vary from lesser on the pressure side (36) to greater on the suction side (38) of the airfoil. A collar portion (52) of the platform provides sufficient contact area for connection stability.
摘要翻译：具有朝向翼型的端部（43）逐渐变细（44）的端部（42）的涡轮机翼（31）。脊（46）围绕端部延伸。它具有近端（66）和远端（67）侧面。护罩平台（50）在没有粘合的情况下双向铸造在脊的端部上。冷却将平台收缩在翼型件的端部（42）上的压缩（62）中。翼型和平台之间的间隙是在双浇铸阶段使用一种短暂的材料（56）形成的。这些间隙与锥角（44）结合设计，以适应不同的热膨胀，同时沿着接触表面保持气体密封。锥形角（44）可以在翼型的吸力侧（38）上的压力侧（36）上较小地变化到更大。平台的凸缘部分（52）为连接稳定性提供了足够的接触面积。

3. 发明申请

US20110243724A1 TURBINE AIRFOIL TO SHROUND ATTACHMENT 失效
标题翻译：涡轮机空气对SHROUND附件
公开(公告)号：US20110243724A1
公开(公告)日：2011-10-06
申请号：US12752460
申请日：2010-04-01
申请人： Christian X. Campbell , Jay A. Morrison , Allister W. James , Raymond G. Snider , Daniel M. Eshak , John J. Marra , Brian J. Wessell
发明人： Christian X. Campbell , Jay A. Morrison , Allister W. James , Raymond G. Snider , Daniel M. Eshak , John J. Marra , Brian J. Wessell
IPC分类号： F01D9/04 , F01D9/02 , B22D19/00
CPC分类号： F01D11/005 , B22D19/00 , B22D19/0081 , F01D9/044 , F05D2230/21 , F05D2240/80
摘要： A turbine airfoil (31) with an end portion (42) that tapers (44) toward the end (43) of the airfoil. A ridge (46) extends around the end portion. It has proximal (66) and distal (67) sides. A shroud platform (50) is bi-cast onto the end portion around the ridge without bonding. Cooling shrinks the platform into compression (62) on the end portion (42) of the airfoil. Gaps between the airfoil and platform are formed using a fugitive material (56) in the bi-casting stage. These gaps are designed in combination with the taper angle (44) to accommodate differential thermal expansion while maintaining a gas seal along the contact surfaces. The taper angle (44) may vary from lesser on the pressure side (36) to greater on the suction side (38) of the airfoil. A collar portion (52) of the platform provides sufficient contact area for connection stability.
摘要翻译：具有朝向翼型的端部（43）逐渐变细（44）的端部（42）的涡轮机翼（31）。脊（46）围绕端部延伸。它具有近端（66）和远端（67）侧面。护罩平台（50）在没有粘合的情况下双向铸造在脊的端部上。冷却将平台收缩在翼型件的端部（42）上的压缩（62）中。翼型和平台之间的间隙是在双浇铸阶段使用一种短暂的材料（56）形成的。这些间隙与锥角（44）结合设计，以适应不同的热膨胀，同时沿着接触表面保持气体密封。锥形角（44）可以在翼型的吸力侧（38）上的压力侧（36）上较小地变化到更大。平台的凸缘部分（52）为连接稳定性提供了足够的接触面积。

4. 发明授权

US08231354B2 Turbine engine airfoil and platform assembly 有权
标题翻译：涡轮发动机翼型和平台组装
公开(公告)号：US08231354B2
公开(公告)日：2012-07-31
申请号：US12638034
申请日：2009-12-15
申请人： Christian X. Campbell , Allister W. James , Jay A. Morrison
发明人： Christian X. Campbell , Allister W. James , Jay A. Morrison
IPC分类号： F01D5/30
CPC分类号： B23P15/04 , F01D5/081 , F01D5/147 , F01D5/3007 , F01D11/008 , F05D2230/51 , F05D2230/52 , F05D2240/40 , F05D2260/36 , Y10T29/49337
摘要： A turbine airfoil (22A) is formed by a first process using a first material. A platform (30A) is formed by a second process using a second material that may be different from the first material. The platform (30A) is assembled around a shank (23A) of the airfoil. One or more pins (36A) extend from the platform into holes (28) in the shank (23A). The platform may be formed in two portions (32A, 34A) and placed around the shank, enclosing it. The two platform portions may be bonded to each other. Alternately, the platform (30B) may be cast around the shank (23B) using a metal alloy with better castability than that of the blade and shank, which may be specialized for thermal tolerance. The pins (36A-36D) or holes for them do not extend to an outer surface (31) of the platform, avoiding stress concentrations.
摘要翻译：涡轮机翼片（22A）通过使用第一材料的第一工艺形成。使用可能不同于第一材料的第二材料的第二工艺形成平台（30A）。平台（30A）组装在机翼的柄（23A）周围。一个或多个销（36A）从平台延伸到柄（23A）中的孔（28）中。平台可以形成为两部分（32A，34A）并且围绕柄部放置并包围该平台。两个平台部分可以彼此结合。或者，平台（30B）可以使用具有比刀片和柄部更好的铸造性的金属合金围绕杆（23B）铸造，其可以专用于耐热性。销（36A-36D）或它们的孔不延伸到平台的外表面（31），以避免应力集中。

5. 发明申请

US20110297344A1 TURBINE AIRFOIL TO SHROUD ATTACHMENT METHOD 有权
标题翻译：涡轮机空气对SHROUD附件方法
公开(公告)号：US20110297344A1
公开(公告)日：2011-12-08
申请号：US13195959
申请日：2011-08-02
申请人： Christian X. Campbell , Anand A. Kulkarni , Allister W. James , Brian J. Wessell , Paul J. Gear
发明人： Christian X. Campbell , Anand A. Kulkarni , Allister W. James , Brian J. Wessell , Paul J. Gear
IPC分类号： B22D19/00
CPC分类号： F01D9/044 , B22C9/10 , B22D19/00 , B22D19/0081 , B22D29/001 , F01D11/005 , F05B2230/21 , F05B2240/80 , F05D2230/21 , F05D2240/80 , Y10T29/49321 , Y10T29/4981 , Y10T29/49826 , Y10T29/49982 , Y10T29/49984
摘要： Bi-casting a platform (50) onto an end portion (42) of a turbine airfoil (31) after forming a coating of a fugitive material (56) on the end portion. After bi-casting the platform, the coating is dissolved and removed to relieve differential thermal shrinkage stress between the airfoil and platform. The thickness of the coating is varied around the end portion in proportion to varying amounts of local differential process shrinkage. The coating may be sprayed (76A, 76B) onto the end portion in opposite directions parallel to a chord line (41) of the airfoil or parallel to a mid-platform length (80) of the platform to form respective layers tapering in thickness from the leading (32) and trailing (34) edges along the suction side (36) of the airfoil.
摘要翻译：在端部上形成缓冲材料（56）的涂层之后，将平台（50）压铸在涡轮机翼（31）的端部（42）上。在双面浇铸平台之后，涂层被溶解和去除，以减轻翼型和平台之间的不同的热收缩应力。涂层的厚度随着局部差动过程收缩量的变化量的比例而在端部周围变化。涂层可以在平行于翼型的弦线（41）的平行方向上平行于平台的中平台长度（80）喷射（76A，76B）到端部上，以形成相应的层沿着翼型的吸力侧（36）的引导（32）和尾部（34）边缘。

6. 发明授权

US08914976B2 Turbine airfoil to shroud attachment method 有权
标题翻译：涡轮机翼到护罩附件方法
公开(公告)号：US08914976B2
公开(公告)日：2014-12-23
申请号：US13195959
申请日：2011-08-02
申请人： Christian X. Campbell , Anand A. Kulkarni , Allister W. James , Brian J. Wessell , Paul J. Gear
发明人： Christian X. Campbell , Anand A. Kulkarni , Allister W. James , Brian J. Wessell , Paul J. Gear
IPC分类号： B21K25/00 , B22D19/00 , F01D9/04 , F01D11/00
CPC分类号： F01D9/044 , B22C9/10 , B22D19/00 , B22D19/0081 , B22D29/001 , F01D11/005 , F05B2230/21 , F05B2240/80 , F05D2230/21 , F05D2240/80 , Y10T29/49321 , Y10T29/4981 , Y10T29/49826 , Y10T29/49982 , Y10T29/49984
摘要： Bi-casting a platform (50) onto an end portion (42) of a turbine airfoil (31) after forming a coating of a fugitive material (56) on the end portion. After bi-casting the platform, the coating is dissolved and removed to relieve differential thermal shrinkage stress between the airfoil and platform. The thickness of the coating is varied around the end portion in proportion to varying amounts of local differential process shrinkage. The coating may be sprayed (76A, 76B) onto the end portion in opposite directions parallel to a chord line (41) of the airfoil or parallel to a mid-platform length (80) of the platform to form respective layers tapering in thickness from the leading (32) and trailing (34) edges along the suction side (36) of the airfoil.
摘要翻译：在端部上形成短暂材料（56）的涂层之后，将平台（50）浇铸到涡轮机翼（31）的端部（42）上。在双面浇铸平台之后，涂层被溶解和去除，以减轻翼型和平台之间的不同的热收缩应力。涂层的厚度随着局部差动过程收缩量的变化量的比例而在端部周围变化。涂层可以在平行于翼型的弦线（41）的平行方向上平行于平台的中平台长度（80）喷射（76A，76B）到端部上，以形成相应的层沿着翼型的吸力侧（36）的引导（32）和尾部（34）边缘。

7. 发明授权

US08079821B2 Turbine airfoil with dual wall formed from inner and outer layers separated by a compliant structure 有权
标题翻译：具有由内层和外层形成的具有双壁的涡轮翼型件由顺应结构隔开
公开(公告)号：US08079821B2
公开(公告)日：2011-12-20
申请号：US12435684
申请日：2009-05-05
申请人： Christian X. Campbell , Jay A. Morrison
发明人： Christian X. Campbell , Jay A. Morrison
IPC分类号： F01D5/18
CPC分类号： F01D5/18 , F01D5/147
摘要： A turbine airfoil usable in a turbine engine with a cooling system and a compliant dual wall configuration configured to enable thermal expansion between inner and outer layers while eliminating stress formation is disclosed. The compliant dual wall configuration may be formed a dual wall formed from inner and outer layers separated by a compliant structure. The compliant structure may be configured such that the outer layer may thermally expand without limitation by the inner layer. The compliant structure may be formed from a plurality of pedestals positioned generally parallel with each other. The pedestals may include a first foot attached to a first end of the pedestal and extending in a first direction aligned with the outer layer, and may include a second foot attached to a second end of the pedestal and extending in a second direction aligned with the inner layer.
摘要翻译：公开了一种可用于具有冷却系统的涡轮发动机的涡轮机翼型和被配置为在消除应力形成的同时在内层和外层之间实现热膨胀的顺应双壁结构。兼容的双壁结构可以形成由内层和外层形成的双层壁，其由柔顺结构隔开。顺应性结构可以被配置为使得外层可以热膨胀而不受内层的限制。柔性结构可以由大体上彼此平行地定位的多个基座形成。基座可以包括附接到基座的第一端并沿着与外层对准的第一方向延伸的第一脚，并且可以包括附接到基座的第二端并沿与第二脚对准的第二方向延伸的第二脚内层。

8. 发明授权

US08251652B2 Gas turbine vane platform element 有权
标题翻译：燃气轮机叶片平台元件
公开(公告)号：US08251652B2
公开(公告)日：2012-08-28
申请号：US12479082
申请日：2009-06-05
申请人： Christian X. Campbell , Anthony L. Schiavo , Jay A. Morrison
发明人： Christian X. Campbell , Anthony L. Schiavo , Jay A. Morrison
IPC分类号： F01D9/04
CPC分类号： F01D9/041 , F01D5/189 , F01D5/282 , F01D5/284 , F05D2300/21 , F05D2300/603 , Y10T29/49323
摘要： A gas turbine CMC shroud plate (48A) with a vane-receiving opening (79) that matches a cross-section profile of a turbine vane airfoil (22). The shroud plate (48A) has first and second curved circumferential sides (73A, 74A) that generally follow the curves of respective first and second curved sides (81, 82) of the vane-receiving opening. Walls (75A, 76A, 77A, 78A, 80, 88) extend perpendicularly from the shroud plate forming a cross-bracing structure for the shroud plate. A vane (22) may be attached to the shroud plate by pins (83) or by hoop-tension rings (106) that clamp tabs (103) of the shroud plate against bosses (105) of the vane. A circular array (20) of shroud plates (48A) may be assembled to form a vane shroud ring in which adjacent shroud plates are separated by compressible ceramic seals (93).
摘要翻译：具有与涡轮机叶片（22）的横截面轮廓匹配的叶片接收开口（79）的燃气轮机CMC护罩板（48A）。护罩板（48A）具有通常沿着叶片接收开口的相应的第一和第二弯曲侧面（81,82）的曲线的第一和第二弯曲周向侧面（73A，74A）。壁（75A，76A，77A，78A，80,88）从罩板垂直延伸，形成用于护罩板的交叉支撑结构。叶片（22）可以通过销（83）或环形张力环（106）附接到护罩板，所述环向张力环将护罩板的突片（103）夹紧在叶片的凸台（105）上。护罩板（48A）的圆形阵列（20）可以组装成形成叶片护罩环，相邻的护板通过可压缩的陶瓷密封件（93）分开。

9. 发明授权

US07435058B2 Ceramic matrix composite vane with chordwise stiffener 有权
标题翻译：陶瓷基复合叶片与弦加强筋
公开(公告)号：US07435058B2
公开(公告)日：2008-10-14
申请号：US11036990
申请日：2005-01-18
申请人： Christian X. Campbell , Harry A. Albrecht , Yevgeniy Shteyman , Jay A. Morrison
发明人： Christian X. Campbell , Harry A. Albrecht , Yevgeniy Shteyman , Jay A. Morrison
IPC分类号： F01D5/18
CPC分类号： F01D5/187 , F01D5/14 , F01D5/282 , F01D5/284 , F05D2260/2214 , F05D2260/22141 , F05D2300/21 , F05D2300/603
摘要： A means (22) for structurally stiffening or reinforcing a ceramic matrix composite (CMC) gas turbine component, such as an airfoil-shaped component, is provided. This structural stiffening or reinforcing of the airfoil allows for reducing bending stress that may be produced from internal or external pressurization of the airfoil without incurring any substantial thermal stress. The stiffener is disposed on a CMC wall and generally extends along a chord length of the airfoil.
摘要翻译：提供了一种用于结构上加强或加强陶瓷基体复合材料（CMC）燃气轮机部件（例如翼型件）的装置（22）。翼型的这种结构加强或加强允许减小由翼型件的内部或外部加压产生的弯曲应力，而不会引起任何实质的热应力。加强筋设置在CMC壁上，并且通常沿翼型的翼弦长度延伸。

10. 发明申请

US20080181766A1 CERAMIC MATRIX COMPOSITE VANE WITH CHORDWISE STIFFENER 有权
标题翻译：陶瓷矩阵复合风扇与CHORDWISE STIFFENER
公开(公告)号：US20080181766A1
公开(公告)日：2008-07-31
申请号：US11036990
申请日：2005-01-18
申请人： Christian X. Campbell , Harry A. Albrecht , Yevgeniy Shteyman , Jay A. Morrison
发明人： Christian X. Campbell , Harry A. Albrecht , Yevgeniy Shteyman , Jay A. Morrison
IPC分类号： F04D31/00
CPC分类号： F01D5/187 , F01D5/14 , F01D5/282 , F01D5/284 , F05D2260/2214 , F05D2260/22141 , F05D2300/21 , F05D2300/603
摘要： A means (22) for structurally stiffening or reinforcing a ceramic matrix composite (CMC) gas turbine component, such as an airfoil-shaped component, is provided. This structural stiffening or reinforcing of the airfoil allows for reducing bending stress that may be produced from internal or external pressurization of the airfoil without incurring any substantial thermal stress. The stiffener is disposed on a CMC wall and generally extends along a chord length of the airfoil.
摘要翻译：提供了一种用于结构上加强或增强陶瓷基体复合材料（CMC）燃气轮机部件如机翼形部件的装置（22）。翼型的这种结构加强或加强允许减小由翼型件的内部或外部加压产生的弯曲应力，而不会引起任何实质的热应力。加强筋设置在CMC壁上，并且通常沿翼型的翼弦长度延伸。

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