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公开(公告)号：US20110194943A1
公开(公告)日：2011-08-11
申请号：US13023651
申请日：2011-02-09
CPC分类号： F01D5/187 , F01D5/22 , F05D2260/221
摘要： A turbine blade assembly in a turbine engine. The turbine blade assembly includes a turbine blade and a first snubber structure. The turbine blade includes an internal cooling passage containing cooling air. The first snubber structure extends outwardly from a sidewall of the turbine blade and includes a hollow interior portion that receives cooling air from the internal cooling passage of the turbine blade.
摘要翻译： 涡轮发动机中的涡轮叶片组件。 涡轮叶片组件包括涡轮叶片和第一缓冲结构。 涡轮机叶片包括内部冷却通道，其包含冷却空气。 第一缓冲结构从涡轮机叶片的侧壁向外延伸并且包括从涡轮叶片的内部冷却通道接收冷却空气的中空内部部分。
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公开(公告)号：US08684692B2
公开(公告)日：2014-04-01
申请号：US13023651
申请日：2011-02-09
CPC分类号： F01D5/187 , F01D5/22 , F05D2260/221
摘要： A turbine blade assembly in a turbine engine. The turbine blade assembly includes a turbine blade and a first snubber structure. The turbine blade includes an internal cooling passage containing cooling air. The first snubber structure extends outwardly from a sidewall of the turbine blade and includes a hollow interior portion that receives cooling air from the internal cooling passage of the turbine blade.
摘要翻译： 涡轮发动机中的涡轮叶片组件。 涡轮叶片组件包括涡轮叶片和第一缓冲结构。 涡轮机叶片包括内部冷却通道，其包含冷却空气。 第一缓冲结构从涡轮机叶片的侧壁向外延伸并且包括从涡轮叶片的内部冷却通道接收冷却空气的中空内部部分。
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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：US20150003973A1
公开(公告)日：2015-01-01
申请号：US13930482
申请日：2013-06-28
申请人： Ching-Pang Lee , Kok-Mun Tham , Eric Schroeder , Jamie Meeroff , Samuel R. Miller, Jr. , John J. Marra , Christian X. Campbell
发明人： Ching-Pang Lee , Kok-Mun Tham , Eric Schroeder , Jamie Meeroff , Samuel R. Miller, Jr. , John J. Marra , Christian X. Campbell
摘要： An outer rim seal arrangement (10), including: an annular rim (70) centered about a longitudinal axis (30) of a rotor disc (31), extending fore and having a fore-end (72), an outward-facing surface (74), and an inward-facing surface (76); a lower angel wing (62) extending aft from a base of a turbine blade (22) and having an aft end (64) disposed radially inward of the rim inward-facing surface to define a lower angel wing seal gap (80); an upper angel wing (66) extending aft from the turbine blade base and having an aft end (68) disposed radially outward of the rim outward-facing surface to define a upper angel wing seal gap (80, 82); and guide vanes (100) disposed on the rim inward-facing surface in the lower angel wing seal gap. Pumping fins (102) may be disposed on the upper angel wing seal aft end in the upper angel wing seal gap.
摘要翻译： 外缘密封装置（10），包括：以转子盘（31）的纵向轴线（30）为中心的环形边缘（70），其在前面延伸并具有前端（72），面向外的表面 （74）和面向内的表面（76）; 从天线叶片（22）的底部向后延伸的下部天使翼（62），并且具有设置在所述边缘向内相对表面的径向内侧的后端（64），以限定下部天使翼密封间隙（80）; 从所述涡轮叶片基部向后延伸的上天使翼（66），并且具有设置在所述轮缘朝外的表面的径向外侧的后端（68），以限定上天使翼密封间隙（80,82）; 以及设置在下天使翼密封间隙中的边缘向内表面上的导向叶片（100）。 抽吸翼（102）可以设置在上天使翼密封间隙中的上天使翼密封后端。
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公开(公告)号：US08579593B2
公开(公告)日：2013-11-12
申请号：US12613957
申请日：2009-11-06
CPC分类号： F01D5/16 , F05D2260/20 , F05D2300/21 , F05D2300/603
摘要： An airfoil (10) is provided with a tip (12) having an opening (14) to a center channel (24). A damping element (16) is inserted within the opening of the center channel, to reduce an induced vibration of the airfoil. The mass of the damping element, a spring constant of the damping element within the center channel, and/or a mounting location (58) of the damping element within the center channel may be adjustably varied, to shift a resonance frequency of the airfoil outside a natural operating frequency of the airfoil.
摘要翻译： 机翼（10）设置有具有到中心通道（24）的开口（14）的尖端（12）。 阻尼元件（16）插入在中心通道的开口内，以减少翼型的感应振动。 缓冲元件的质量，中心通道内的阻尼元件的弹簧常数和/或中心通道内的阻尼元件的安装位置（58）可以可调地变化，以使翼型件的共振频率向外移动 机翼的自然工作频率。
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公开(公告)号：US09017014B2
公开(公告)日：2015-04-28
申请号：US13930482
申请日：2013-06-28
申请人： Ching-Pang Lee , Kok-Mun Tham , Eric Schroeder , Jamie Meeroff , Samuel R. Miller, Jr. , John J. Marra , Christian X. Campbell
发明人： Ching-Pang Lee , Kok-Mun Tham , Eric Schroeder , Jamie Meeroff , Samuel R. Miller, Jr. , John J. Marra , Christian X. Campbell
摘要： An outer rim seal arrangement (10), including: an annular rim (70) centered about a longitudinal axis (30) of a rotor disc (31), extending fore and having a fore-end (72), an outward-facing surface (74), and an inward-facing surface (76); a lower angel wing (62) extending aft from a base of a turbine blade (22) and having an aft end (64) disposed radially inward of the rim inward-facing surface to define a lower angel wing seal gap (80); an upper angel wing (66) extending aft from the turbine blade base and having an aft end (68) disposed radially outward of the rim outward-facing surface to define a upper angel wing seal gap (80, 82); and guide vanes (100) disposed on the rim inward-facing surface in the lower angel wing seal gap. Pumping fins (102) may be disposed on the upper angel wing seal aft end in the upper angel wing seal gap.
摘要翻译： 外缘密封装置（10），包括：以转子盘（31）的纵向轴线（30）为中心的环形边缘（70），其在前面延伸并具有前端（72），面向外的表面 （74）和面向内的表面（76）; 从天线叶片（22）的底部向后延伸的下部天使翼（62），并且具有设置在所述边缘向内相对表面的径向内侧的后端（64），以限定下部天使翼密封间隙（80）; 从所述涡轮叶片基部向后延伸的上天使翼（66），并且具有设置在所述轮缘朝外的表面的径向外侧的后端（68），以限定上天使翼密封间隙（80,82）; 以及设置在下天使翼密封间隙中的边缘向内表面上的导向叶片（100）。 抽吸翼（102）可以设置在上天使翼密封间隙中的上天使翼密封后端。
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公开(公告)号：US20110110762A1
公开(公告)日：2011-05-12
申请号：US12613957
申请日：2009-11-06
CPC分类号： F01D5/16 , F05D2260/20 , F05D2300/21 , F05D2300/603
摘要： An airfoil (10) is provided with a tip (12) having an opening (14) to a center channel (24). A damping element (16) is inserted within the opening of the center channel, to reduce an induced vibration of the airfoil. The mass of the damping element, a spring constant of the damping element within the center channel, and/or a mounting location (58) of the damping element within the center channel may be adjustably varied, to shift a resonance frequency of the airfoil outside a natural operating frequency of the airfoil.
摘要翻译： 机翼（10）设置有具有到中心通道（24）的开口（14）的尖端（12）。 阻尼元件（16）插入在中心通道的开口内，以减少翼型的感应振动。 缓冲元件的质量，中心通道内的阻尼元件的弹簧常数和/或中心通道内的阻尼元件的安装位置（58）可以可调地变化，以使翼型件的共振频率向外移动 机翼的自然工作频率。
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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
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。
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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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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
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。
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