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1.发明申请公开(公告)号：US20120237786A1
公开(公告)日：2012-09-20
申请号：US13050057
申请日：2011-03-17
CPC分类号： F01D25/12 , B22D19/00 , B22D19/04 , B32B15/01 , F01D25/005 , F23R2900/00018 , F28F3/12 , Y10T29/4932 , Y10T29/49616 , Y10T29/49988 , Y10T428/12361 , Y10T428/12479
摘要： A structural layer (30) may be bi-cast onto ligaments (62) extending from a porous cooling construction (20). The material of the structural layer may be optimized for high-temperature strength, while the material of the porous construction may be optimized for high thermal conductivity. A fugitive material (56) such as wax may be formed on the ligaments of the porous construction. A second fugitive material (58) such as ceramic may fill the remaining part of the porous construction. An investment casting shell (60) may be disposed around the porous construction and the fugitive materials. The first fugitive material may then be replaced with the material of the structural layer (30), and the second fugitive material may be removed to provide coolant paths (26). A second structural layer (52) may be bi-cast onto further ligaments (62) on a second side of the porous construction.
摘要翻译： 结构层（30）可以双向浇铸到从多孔冷却结构（20）延伸的韧带（62）上。 结构层的材料可以针对高温强度进行优化，而多孔结构的材料可以针对高热导率而被优化。 可以在多孔结构的韧带上形成诸如蜡的短暂材料（56）。 诸如陶瓷的第二短暂材料（58）可以填充多孔结构的剩余部分。 投资铸造外壳（60）可围绕多孔结构和逸散材料设置。 然后可以用结构层（30）的材料代替第一短暂材料，并且可以去除第二短暂材料以提供冷却剂路径（26）。 第二结构层（52）可以双向浇铸到多孔结构的第二侧上的另外的韧带（62）上。
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2.发明授权公开(公告)号：US08793871B2
公开(公告)日：2014-08-05
申请号：US13050057
申请日：2011-03-17
IPC分类号： B21K25/00
CPC分类号： F01D25/12 , B22D19/00 , B22D19/04 , B32B15/01 , F01D25/005 , F23R2900/00018 , F28F3/12 , Y10T29/4932 , Y10T29/49616 , Y10T29/49988 , Y10T428/12361 , Y10T428/12479
摘要： A structural layer (30) may be bi-cast onto ligaments (62) extending from a porous cooling construction (20). The material of the structural layer may be optimized for high-temperature strength, while the material of the porous construction may be optimized for high thermal conductivity. A fugitive material (56) such as wax may be formed on the ligaments of the porous construction. A second fugitive material (58) such as ceramic may fill the remaining part of the porous construction. An investment casting shell (60) may be disposed around the porous construction and the fugitive materials. The first fugitive material may then be replaced with the material of the structural layer (30), and the second fugitive material may be removed to provide coolant paths (26). A second structural layer (52) may be bi-cast onto further ligaments (62) on a second side of the porous construction.
摘要翻译： 结构层（30）可以双向浇铸到从多孔冷却结构（20）延伸的韧带（62）上。 结构层的材料可以针对高温强度进行优化，而多孔结构的材料可以针对高热导率而被优化。 可以在多孔结构的韧带上形成诸如蜡的短暂材料（56）。 诸如陶瓷的第二短暂材料（58）可以填充多孔结构的剩余部分。 投资铸造外壳（60）可围绕多孔结构和逸散材料设置。 然后可以用结构层（30）的材料代替第一短暂材料，并且可以去除第二短暂材料以提供冷却剂路径（26）。 第二结构层（52）可以双向浇铸到多孔结构的第二侧上的另外的韧带（62）上。
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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：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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5.发明授权Method of forming a multi-panel outer wall of a component for use in a gas turbine engine 有权形成用于燃气涡轮发动机的部件的多面板外壁的方法公开(公告)号：US08727714B2
公开(公告)日：2014-05-20
申请号：US13094948
申请日：2011-04-27
申请人： Raymond G. Snider , Jay A. Morrison
发明人： Raymond G. Snider , Jay A. Morrison
IPC分类号： F01D25/26
CPC分类号： F01D9/023 , F01D25/12 , F05D2230/60 , F05D2260/201 , F23R3/002 , F23R2900/00017 , F23R2900/03044 , Y10T29/49323 , Y10T29/49879
摘要： A method of forming and/or assembling a multi-panel outer wall (14) for a component (12) in a machine subjected to high thermal stresses comprising providing such a component (12) that includes an inner panel wall (16) having an outer surface, and an array of interconnecting ribs (38) on the outer surface of the component (12). An intermediate panel (22) is provided and preferably preformed to a general outer contour of the component (12), and is positioned over the inner panel (16). An external pressure force is applied across a surface area of the intermediate panel (22) against the outer surface of the component (12) to contour the intermediate panel (22) according to a geometric configuration formed by the ribs (38) thereby forming cooling chambers (24) between the outer surface and ribs (38) of the component (12) and the intermediate panel (22).
摘要翻译： 一种在经受高热应力的机器中形成和/或组装用于部件（12）的多面板外壁（14）的方法，包括提供这样的部件（12），所述部件包括内板壁（16） 外表面和在组件（12）的外表面上的互连肋（38）的阵列。 中间板（22）设置并优选地预成型为部件（12）的一般外轮廓，并且定位在内板（16）上。 根据由肋（38）形成的几何构型，外部压力力跨过中间板（22）的表面区域施加到部件（12）的外表面，以使中间板（22）轮廓化，从而形成冷却 在组件（12）的外表面和肋（38）和中间板（22）之间的腔室（24）。
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6.发明申请METHOD OF FORMING A MULTI-PANEL OUTER WALL OF A COMPONENT FOR USE IN A GAS TURBINE ENGINE 有权用于气体涡轮发动机的组件的多面板外壁的形成方法公开(公告)号：US20120275900A1
公开(公告)日：2012-11-01
申请号：US13094948
申请日：2011-04-27
申请人： Raymond G. Snider , Jay A. Morrison
发明人： Raymond G. Snider , Jay A. Morrison
CPC分类号： F01D9/023 , F01D25/12 , F05D2230/60 , F05D2260/201 , F23R3/002 , F23R2900/00017 , F23R2900/03044 , Y10T29/49323 , Y10T29/49879
摘要： A method of forming and/or assembling a multi-panel outer wall (14) for a component (12) in a machine subjected to high thermal stresses comprising providing such a component (12) that includes an inner panel wall (16) having an outer surface, and an array of interconnecting ribs (38) on the outer surface of the component (12). An intermediate panel (22) is provided and preferably preformed to a general outer contour of the component (12), and is positioned over the inner panel (16). An external pressure force is applied across a surface area of the intermediate panel (22) against the outer surface of the component (12) to contour the intermediate panel (22) according to a geometric configuration formed by the ribs (38) thereby forming cooling chambers (24) between the outer surface and ribs (38) of the component (12) and the intermediate panel (22).
摘要翻译： 一种在经受高热应力的机器中形成和/或组装用于部件（12）的多面板外壁（14）的方法，包括提供这样的部件（12），所述部件包括内板壁（16） 外表面和在组件（12）的外表面上的互连肋（38）的阵列。 中间板（22）设置并优选地预成型为部件（12）的一般外轮廓，并且定位在内板（16）上。 根据由肋（38）形成的几何构型，外部压力力跨过中间板（22）的表面区域施加到部件（12）的外表面，以使中间板（22）轮廓化，从而形成冷却 在组件（12）的外表面和肋（38）和中间板（22）之间的腔室（24）。
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公开(公告)号：US5330711A
公开(公告)日：1994-07-19
申请号：US927497
申请日：1992-09-29
申请人： Raymond G. Snider
发明人： Raymond G. Snider
CPC分类号： C22C19/056 , C22F1/10
摘要： A nickel-base casting alloy for use in gas turbine components consists essentially of the composition (in weight percent): carbon 0.02-0.15, chromium 14-18, cobalt 8-12, aluminum 0.5-1.5, titanium 2.0-3.5, niobium 3.5-6.0, tantalum 1.0-2.0, tungsten 1.0-3.0, molybdenum 3.0-6.0, boron 0.002-0.05, zirconium 0.01-0.1, balance nickel and incidental impurities. The alloy is characterized by a volume fraction of gamma prime of about 32%, an ultimate tensile strength in the range 990-1010 MPa over the temperature range 550.degree.-750.degree. C., and a mean coefficient of linear thermal expansion in the range 11.5-15.0 alpha(*E-06/.degree.C.).
摘要翻译： PCT No.PCT / GB92 / 00228 Sec。 371日期：1992年9月29日 102（e）1992年9月29日PCT 1992年2月6日PCT。用于燃气轮机部件的镍基铸造合金主要由组合物（重量百分比）组成：碳0.02-0.15，铬14-18 ，钴8-12，铝0.5-1.5，钛2.0-3.5，铌3.5-6.0，钽1.0-2.0，钨1.0-3.0，钼3.0-6.0，硼0.002-0.05，锆0.01-0.1，余量镍和附带的 杂质。 该合金的特征在于γ射线的体积分数为约32％，极限拉伸强度在550℃-750℃的温度范围内为990-1010MPa，线性热膨胀系数为 11.5-15.0α（* E-06 /℃）。
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