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公开(公告)号：US08939727B2
公开(公告)日：2015-01-27
申请号：US13227603
申请日：2011-09-08
申请人： Christian X. Campbell , Darryl Eng , John J. Marra
发明人： Christian X. Campbell , Darryl Eng , John J. Marra
CPC分类号： F01D11/008 , F01D5/3007
摘要： Platforms (36, 38) span between turbine blades (23, 24, 25) on a disk (32). Each platform may be individually mounted to the disk by a pin attachment (42). Each platform (36) may have a rotationally rearward edge portion (50) that underlies a forward portion (45) of the adjacent platform (38). This limits centrifugal bending of the rearward portion of the platform, and provides coolant sealing. The rotationally forward edge (44A, 44B) of the platform overlies a seal element (51) on the pressure side (28) of the forwardly adjacent blade, and does not underlie a shelf on that blade. The pin attachment allows radial mounting of each platform onto the disk via tilting (60) of the platform during mounting to provide mounting clearance for the rotationally rearward edge portion (50). This facilitates quick platform replacement without blade removal.
摘要翻译： 平台（36,38）跨越盘（32）上的涡轮叶片（23,24,25）之间。 每个平台可以通过销附件（42）单独地安装到盘上。 每个平台（36）可以具有在相邻平台（38）的前部（45）下面的旋转后边缘部分（50）。 这限制了平台后部的离心弯曲，并提供冷却剂密封。 平台的旋转前缘（44A，44B）覆盖在前方相邻叶片的压力侧（28）上的密封元件（51）上，并且不位于该刀片上的搁板的下面。 销安装件允许在安装期间通过平台的倾斜（60）将每个平台径向地安装到盘上，以为旋转后边缘部分（50）提供安装间隙。 这有助于快速平台更换，而无需拆卸刀片。
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公开(公告)号：US20130064667A1
公开(公告)日：2013-03-14
申请号：US13227603
申请日：2011-09-08
申请人： Christian X. Campbell , Darryl Eng , John J. Marra
发明人： Christian X. Campbell , Darryl Eng , John J. Marra
IPC分类号： F01D5/30
CPC分类号： F01D11/008 , F01D5/3007
摘要： Platforms (36, 38) span between turbine blades (23, 24, 25) on a disk (32). Each platform may be individually mounted to the disk by a pin attachment (42). Each platform (36) may have a rotationally rearward edge portion (50) that underlies a forward portion (45) of the adjacent platform (38). This limits centrifugal bending of the rearward portion of the platform, and provides coolant sealing. The rotationally forward edge (44A, 44B) of the platform overlies a seal element (51) on the pressure side (28) of the forwardly adjacent blade, and does not underlie a shelf on that blade. The pin attachment allows radial mounting of each platform onto the disk via tilting (60) of the platform during mounting to provide mounting clearance for the rotationally rearward edge portion (50). This facilitates quick platform replacement without blade removal.
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3.发明申请公开(公告)号：US20110142639A1
公开(公告)日：2011-06-16
申请号：US12793935
申请日：2010-06-04
CPC分类号： F01D5/147 , F01D5/081 , F01D5/3007 , F01D11/008
摘要： A turbine airfoil (22E-H) extends from a shank (23E-H). A platform (30E-H) brackets or surrounds a first portion of the shank (23E-H). Opposed teeth (33, 35) extend laterally from the platform (30E-H) to engage respective slots (50) in a disk. Opposed teeth (25, 27) extend laterally from a second portion of the shank (29) that extends below the platform (30E-H) to engage other slots (52) in the disk. Thus the platform (30E-H) and the shank (23E-H) independently support their own centrifugal loads via their respective teeth. The platform may be formed in two portions (32E-H, 34E-H), that are bonded to each other at matching end-walls (37) and/or via pins (36G) passing through the shank (23E-H). Coolant channels (41, 43) may pass through the shank beside the pins (36G).
摘要翻译： 涡轮机翼（22E-H）从柄（23E-H）延伸。 平台（30E-H）支架或围绕柄部（23E-H）的第一部分。 相对的齿（33,35）从平台（30E-H）横向地延伸以与盘中的相应的槽（50）接合。 相对的齿（25,27）从在所述平台（30E-H）下方延伸的所述柄（29）的第二部分横向延伸，以接合所述盘中的其它狭槽（52）。 因此，平台（30E-H）和柄（23E-H）通过其相应的齿独立地支撑它们自己的离心载荷。 平台可以形成为两个部分（32E-H，34E-H），它们在通过柄（23E-H）的匹配端壁（37）和/或通孔销（36G）处彼此结合。 冷却剂通道（41,43）可以穿过销（36G）旁边的柄。
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公开(公告)号：US08814507B1
公开(公告)日：2014-08-26
申请号：US13903087
申请日：2013-05-28
申请人： Christian X Campbell , Darryl Eng , Ching-Pang Lee , Harry Patat
发明人： Christian X Campbell , Darryl Eng , Ching-Pang Lee , Harry Patat
IPC分类号： F01D25/12
CPC分类号： F01D25/12 , F01D5/08 , F01D11/24 , F01D25/14 , F01D25/24 , F05D2240/11 , F05D2260/201
摘要： A triple hook ring segment including forward, midsection and aft mounting hooks for engagement with respective hangers formed on a ring segment carrier for supporting a ring segment panel, and defining a forward high pressure chamber and an aft low pressure chamber on opposing sides of the midsection mounting hook. An isolation plate is provided on the aft side of the midsection mounting hook to form an isolation chamber between the aft low pressure chamber and the ring segment panel. High pressure air is supplied to the forward chamber and flows to the isolation chamber through crossover passages in the midsection hook. The isolation chamber provides convection cooling air to an aft portion of the ring segment panel and enables a reduction of air pressure in the aft low pressure chamber to reduce leakage flow of cooling air from the ring segment.
摘要翻译： 三钩环段，包括前，中，后安装钩，用于与形成在环形段载体上的相应悬挂架相接合，用于支撑环形段板，并且在中央部分的相对侧上限定向前的高压室和后部低压室 挂钩。 在中央安装钩的后侧设置有隔离板，以在后低压室和环形段面板之间形成隔离室。 高压空气被供给到前向室，并且通过中段钩中的交叉通道流入隔离室。 隔离室将对流冷却空气提供给环形区段面板的后部，并且能够减小后部低压室中的空气压力，以减少来自环形段的冷却空气的泄漏流。
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5.发明授权公开(公告)号：US08496443B2
公开(公告)日：2013-07-30
申请号：US12793935
申请日：2010-06-04
IPC分类号： F01D5/30
CPC分类号： F01D5/147 , F01D5/081 , F01D5/3007 , F01D11/008
摘要： A turbine airfoil (22E-H) extends from a shank (23E-H). A platform (30E-H) brackets or surrounds a first portion of the shank (23E-H). Opposed teeth (33, 35) extend laterally from the platform (30E-H) to engage respective slots (50) in a disk. Opposed teeth (25, 27) extend laterally from a second portion of the shank (29) that extends below the platform (30E-H) to engage other slots (52) in the disk. Thus the platform (30E-H) and the shank (23E-H) independently support their own centrifugal loads via their respective teeth. The platform may be formed in two portions (32E-H, 34E-H), that are bonded to each other at matching end-walls (37) and/or via pins (36G) passing through the shank (23E-H). Coolant channels (41, 43) may pass through the shank beside the pins (36G).
摘要翻译： 涡轮机翼（22E-H）从柄（23E-H）延伸。 平台（30E-H）支架或围绕柄部（23E-H）的第一部分。 相对的齿（33,35）从平台（30E-H）横向地延伸以与盘中的相应的槽（50）接合。 相对的齿（25,27）从在所述平台（30E-H）下方延伸的所述柄（29）的第二部分横向延伸，以接合所述盘中的其它狭槽（52）。 因此，平台（30E-H）和柄（23E-H）通过其相应的齿独立地支撑它们自己的离心载荷。 平台可以形成为两个部分（32E-H，34E-H），它们在通过柄（23E-H）的匹配端壁（37）和/或通孔销（36G）处彼此结合。 冷却剂通道（41,43）可以穿过销（36G）旁边的柄。
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