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1.发明申请Method of Making a Combustion Turbine Component from Metallic Combustion Turbine Subcomponent Greenbodies 审中-公开制造来自金属燃烧涡轮机组件燃烧涡轮机部件的方法公开(公告)号：US20090183850A1
公开(公告)日：2009-07-23
申请号：US12238774
申请日：2008-09-26
申请人： Jay A. Morrison , Jay E. Lane , Allister W. James
发明人： Jay A. Morrison , Jay E. Lane , Allister W. James
IPC分类号： B22D17/00
CPC分类号： B22F7/062 , B22F3/1055 , B22F5/009 , B22F2005/005 , B22F2998/00 , B22F2998/10 , F05B2230/22 , Y02P10/295 , Y10T156/10 , B22F3/008 , B22F3/225 , B22F3/10
摘要： A method of making a combustion turbine component includes assembling a plurality of metallic combustion turbine subcomponent greenbodies together to form a metallic greenbody assembly and sintering the metallic greenbody assembly to thereby form the combustion turbine component. Each of the plurality of metallic combustion turbine subcomponent greenbodies may be formed by direct metal fabrication (DMF). In addition, each of plurality of metallic combustion turbine subcomponent greenbodies may include an activatable binder and the activatable binder may be activated prior to sintering.
摘要翻译： 制造燃气轮机部件的方法包括将多个金属燃料涡轮机副部件生物体组装在一起以形成金属生坯体组件并烧结金属生坯体组件，从而形成燃气轮机部件。 多个金属燃料涡轮机副部件生态体中的每一个可以通过直接金属制造（DMF）形成。 此外，多个金属燃料涡轮机副部件生物体中的每一个可以包括可活化的粘合剂，并且可活化的粘合剂可以在烧结之前被活化。
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2.发明申请Method of Making a Combustion Turbine Component Having a Plurality of Surface Cooling Features and Associated Components 审中-公开制造具有多种表面冷却特性和相关部件的燃烧涡轮机部件的方法公开(公告)号：US20120000072A9
公开(公告)日：2012-01-05
申请号：US12507503
申请日：2009-07-22
申请人： Jay A. Morrison , Jay E. Lane , Allister W. James , Gary B. Merrill , John R. Paulus , Mike P. Appleby , Iain A. Fraser
发明人： Jay A. Morrison , Jay E. Lane , Allister W. James , Gary B. Merrill , John R. Paulus , Mike P. Appleby , Iain A. Fraser
IPC分类号： B21K3/04
CPC分类号： B22F5/009 , B22F3/105 , B22F3/225 , Y10T29/49339
摘要： A method of making a combustion turbine component includes forming a metallic body by direct metal fabrication (DMF) to have at least one surface portion defining a first plurality of surface cooling features each having a first dimension and at least one second surface cooling feature on at least one of the first plurality of surface cooling features and having a second dimension less than said first dimension and less than 200 μm. Forming the metallic body by DMF may include forming a plurality of metallic combustion turbine subcomponent greenbodies by DMF and assembling the plurality of metallic combustion turbine subcomponent greenbodies together to form a metallic greenbody assembly. The metallic greenbody assembly may be sintered to thereby form the metallic body.
摘要翻译： 制造燃气涡轮机部件的方法包括通过直接金属制造（DMF）形成金属体，以具有限定第一多个表面冷却特征的至少一个表面部分，每个具有第一尺寸和至少一个第二表面冷却特征 所述第一多个表面冷却特征中的至少一个具有小于所述第一尺寸且小于200μm的第二尺寸。 通过DMF形成金属体可以包括通过DMF形成多个金属燃料涡轮机副成分的生态体，并将多个金属燃料涡轮机副成分的生物体组装在一起以形成金属生物体组件。 金属生坯组件可以被烧结从而形成金属体。
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3.发明申请Method of Making a Combustion Turbine Component Having a Plurality of Surface Cooling Features and Associated Components 审中-公开制造具有多种表面冷却特性和相关部件的燃烧涡轮机部件的方法公开(公告)号：US20110016717A1
公开(公告)日：2011-01-27
申请号：US12507503
申请日：2009-07-22
申请人： Jay A. Morrison , Jay E. Lane , Allister W. James , Gary B. Merrill , John R. Paulus , Mike P. Appleby , Iain A. Fraser
发明人： Jay A. Morrison , Jay E. Lane , Allister W. James , Gary B. Merrill , John R. Paulus , Mike P. Appleby , Iain A. Fraser
IPC分类号： B21K3/04
CPC分类号： B22F5/009 , B22F3/105 , B22F3/225 , Y10T29/49339
摘要： A method of making a combustion turbine component includes forming a metallic body by direct metal fabrication (DMF) to have at least one surface portion defining a first plurality of surface cooling features each having a first dimension and at least one second surface cooling feature on at least one of the first plurality of surface cooling features and having a second dimension less than said first dimension and less than 200 μm. Forming the metallic body by DMF may include forming a plurality of metallic combustion turbine subcomponent greenbodies by DMF and assembling the plurality of metallic combustion turbine subcomponent greenbodies together to form a metallic greenbody assembly. The metallic greenbody assembly may be sintered to thereby form the metallic body.
摘要翻译： 制造燃气涡轮机部件的方法包括通过直接金属制造（DMF）形成金属体，以具有限定第一多个表面冷却特征的至少一个表面部分，每个具有第一尺寸和至少一个第二表面冷却特征 所述第一多个表面冷却特征中的至少一个具有小于所述第一尺寸且小于200μm的第二尺寸。 通过DMF形成金属体可以包括通过DMF形成多个金属燃料涡轮机副成分的生态体，并将多个金属燃料涡轮机副成分的生物体组装在一起以形成金属生物体组件。 金属生坯组件可以被烧结从而形成金属体。
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公开(公告)号：US20110142684A1
公开(公告)日：2011-06-16
申请号：US12638034
申请日：2009-12-15
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。
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5.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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公开(公告)号：US08231354B2
公开(公告)日：2012-07-31
申请号：US12638034
申请日：2009-12-15
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。
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公开(公告)号：US20110041313A1
公开(公告)日：2011-02-24
申请号：US12545930
申请日：2009-08-24
申请人： Allister W. James , Jay A. Morrison
发明人： Allister W. James , Jay A. Morrison
CPC分类号： F01D9/044 , F05D2230/22 , F05D2250/14 , F05D2250/232 , Y10T29/49321 , Y10T29/49323 , Y10T29/49863 , Y10T29/49865 , Y10T29/49908 , Y10T29/53
摘要： A stem (34) extends from a second part (30) through a hole (28) in a first part (22). A groove (38) around the stem provides a non-threaded contact surface (42) for a ring element (44) around the stem. The ring element exerts an inward force against the non-threaded contact surface at an angle that creates axial tension (T) in the stem, pulling the second part against the first part. The ring element is formed of a material that shrinks relative to the stem by sintering. The ring element may include a split collet (44C) that fits partly into the groove, and a compression ring (44E) around the collet. The non-threaded contact surface and a mating distal surface (48) of the ring element may have conic geometries (64). After shrinkage, the ring element is locked onto the stem.
摘要翻译： 杆（34）从第二部分（30）穿过第一部分（22）中的孔（28）延伸。 围绕杆的凹槽（38）为围绕杆的环形元件（44）提供非螺纹接触表面（42）。 环形元件以产生杆中的轴向张力（T）的角度向非螺纹接触表面施加向内的力，将第二部分拉向第一部分。 环形元件由通过烧结相对于杆收缩的材料形成。 环形元件可以包括部分地配合到凹槽中的分割夹头（44C）和围绕夹头的压缩环（44E）。 环形元件的非螺纹接触表面和配合远端表面（48）可以具有锥形几何形状（64）。 收缩后，环形元件锁定在杆上。
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8.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：US08256088B2
公开(公告)日：2012-09-04
申请号：US12545930
申请日：2009-08-24
申请人： Allister W. James , Jay A. Morrison
发明人： Allister W. James , Jay A. Morrison
CPC分类号： F01D9/044 , F05D2230/22 , F05D2250/14 , F05D2250/232 , Y10T29/49321 , Y10T29/49323 , Y10T29/49863 , Y10T29/49865 , Y10T29/49908 , Y10T29/53
摘要： A stem (34) extends from a second part (30) through a hole (28) in a first part (22). A groove (38) around the stem provides a non-threaded contact surface (42) for a ring element (44) around the stem. The ring element exerts an inward force against the non-threaded contact surface at an angle that creates axial tension (T) in the stem, pulling the second part against the first part. The ring element is formed of a material that shrinks relative to the stem by sintering. The ring element may include a split collet (44C) that fits partly into the groove, and a compression ring (44E) around the collet. The non-threaded contact surface and a mating distal surface (48) of the ring element may have conic geometries (64). After shrinkage, the ring element is locked onto the stem.
摘要翻译： 杆（34）从第二部分（30）穿过第一部分（22）中的孔（28）延伸。 围绕杆的凹槽（38）为围绕杆的环形元件（44）提供非螺纹接触表面（42）。 环形元件以产生杆中的轴向张力（T）的角度向非螺纹接触表面施加向内的力，将第二部分拉向第一部分。 环形元件由通过烧结相对于杆收缩的材料形成。 环形元件可以包括部分地配合到凹槽中的分割夹头（44C）和围绕夹头的压缩环（44E）。 环形元件的非螺纹接触表面和配合远端表面（48）可以具有锥形几何形状（64）。 收缩后，环形元件锁定在杆上。
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