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41. 发明申请

US20120276361A1 HYBRID MANUFACTURING PROCESS AND PRODUCT MADE USING LAMINATED SHEETS AND COMPRESSIVE CASING 有权
标题翻译：混合制造工艺和使用层压片和压缩机的产品
公开(公告)号：US20120276361A1
公开(公告)日：2012-11-01
申请号：US13094985
申请日：2011-04-27
申请人： Allister W. James , Gary B. Merrill , Iain A. Fraser
发明人： Allister W. James , Gary B. Merrill , Iain A. Fraser
IPC分类号： B32B7/08 , B32B38/00 , B32B37/02
CPC分类号： B32B3/266 , B28B1/002 , B32B1/00 , B32B2605/00 , B33Y10/00 , Y10T428/249923
摘要： Fabricating a core of a component (34A, 34B, 34C) from a stack (25, 36) of sheets (20) of material with cutouts (22A) in the sheets aligned to form passages (38) in the core. A casing preform (28) is then fitted over the core. The preform is processed to form a casing (29) that brackets at least parts of opposed ends of the stack. Shrinkage of the casing during processing compresses (46) the sheets together. The preform may slide (52) over the core, and may be segmented (28A, 28B, 28C) to fit over the core. A hoop (66) may be fitted and compressed around the segmented casing (29A, 29B, 29C).
摘要翻译：从片材（20）的堆叠（25,36）制造组件（34A，34B，34C）的芯，其中片材中的切口（22A）被排列成在芯中形成通道（38）。然后将壳体预制件（28）装配在芯上。处理预成型件以形成一个壳体（29），该壳体（29）支撑堆叠的相对端的至少部分。加工过程中外壳的收缩将片材（46）压缩在一起。预制件可以在芯上滑动（52），并且可以被分段（28A，28B，28C）以配合在芯上。箍（66）可以围绕分段的壳体（29A，29B，29C）被安装和压缩。

42. 发明申请

US20120237786A1 PROCESS FOR MAKING A WALL WITH A POROUS ELEMENT FOR COMPONENT COOLING 有权
标题翻译：用于制造具有用于组件冷却的多孔元件的壁的方法
公开(公告)号：US20120237786A1
公开(公告)日：2012-09-20
申请号：US13050057
申请日：2011-03-17
申请人： Jay A. Morrison , Raymond G. Snider , Allister W. James
发明人： Jay A. Morrison , Raymond G. Snider , Allister W. James
IPC分类号： B32B5/18 , B32B3/10 , B32B15/01 , B22D19/00
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。

43. 发明授权

US08241001B2 Stationary turbine component with laminated skin 有权
标题翻译：固定涡轮机组件与层压皮肤
公开(公告)号：US08241001B2
公开(公告)日：2012-08-14
申请号：US12204138
申请日：2008-09-04
申请人： Allister W. James
发明人： Allister W. James
IPC分类号： B63H1/26 , B63H7/02 , B64C27/46 , F01D5/14 , F03B7/00 , F03D11/02 , F04D29/38
CPC分类号： F01D5/147 , F01D5/34 , F01D9/041
摘要： A stationary turbine engine component, such as a turbine vane, includes a internal spar and an external skin. The internal spar is made of a plurality of spar laminates, and the external skin is made of a plurality of skin laminates. The plurality of skin laminates interlockingly engage the plurality of spar laminates such that the external skin is located and held in place. This arrangement allows alternative high temperature materials to be used on turbine engine components in areas where their properties are needed without having to make the entire component out of such material. Thus, the manufacturing difficulties associated with making an entire component of such a material and the attendant high costs are avoided. The skin laminates can be made of advanced generation single crystal superalloys, intermetallics and refractory alloys.
摘要翻译：诸如涡轮叶片的固定涡轮发动机部件包括内部翼梁和外部皮肤。内部翼梁由多个翼梁层叠体制成，并且外部皮肤由多个皮肤层压体制成。多个皮肤层压件互锁地接合多个翼梁层压板，使得外部皮肤定位并保持就位。这种布置允许替代的高温材料在需要其性能的区域中用于涡轮发动机部件上，而不必使整个部件脱离这种材料。因此，避免了与制造这种材料的整个部件相关的制造困难和伴随的高成本。皮革层压板可以由先进的单晶超合金，金属间化合物和耐火合金制成。

44. 发明申请

US20120201685A1 JOINING MECHANISM AND METHOD FOR INTERLOCKING MODULAR TURBINE ENGINE COMPONENT WITH A SPLIT RING 有权
标题翻译：用分体式连接模块化涡轮发动机部件的接合机构和方法
公开(公告)号：US20120201685A1
公开(公告)日：2012-08-09
申请号：US13023721
申请日：2011-02-09
申请人： Gary B. Merrill , Allister W. James , Iain A. Fraser
发明人： Gary B. Merrill , Allister W. James , Iain A. Fraser
IPC分类号： F01D5/32 , B23P11/00
CPC分类号： F01D9/044 , F01D5/147 , F04D29/563 , F04D29/644 , Y02T50/67 , Y02T50/672
摘要： A modular airfoil assembly (200) and related method for interlocking components of an airfoil structure (210) including a platform (220), an airfoil (210) having a shoulder (230) and a stem (232) extending outward from the shoulder. A ring element (100) positioned against the stem (232) secures the shoulder (230) against the platform (210). First and second members (100a, 100b) of the ring element (100) are bonded together with a portion (128j) of a surface (112a) of the second member (100b) extending within and bonded to a portion (128i) of a surface (112b) of the first member (100a).
摘要翻译：一种用于联锁翼型结构（210）的组件的模块化翼型组件（200）和相关方法，该翼型结构包括平台（220），具有从肩部向外延伸的肩部（230）和杆（232）的翼型件（210）。定位在杆（232）上的环形元件（100）将肩部（230）固定在平台（210）上。环形元件（100）的第一和第二构件（100a，100b）与第二构件（100b）的在其内部延伸并结合到其中的部分（128i）的部分（128j）第一构件（100a）的表面（112b）。

45. 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。

46. 发明申请

US20110299999A1 MULTI-COMPONENT ASSEMBLY CASTING 有权
标题翻译：多组分组装铸件
公开(公告)号：US20110299999A1
公开(公告)日：2011-12-08
申请号：US12795002
申请日：2010-06-07
申请人： Allister W. James
发明人： Allister W. James
IPC分类号： F01D5/18 , B22D19/00 , B23P15/02 , B23P15/04 , F03B3/12 , B64C27/46
CPC分类号： B22D19/00 , B22C9/04 , C22C19/03 , F01D5/147 , F01D5/187 , F01D5/28 , F05D2230/211 , F05D2300/607 , Y10T29/4932 , Y10T29/49341
摘要： Multi-component vane segment and method for forming the same. Assembly includes: positioning a pre-formed airfoil component (12) and a preformed shroud heat resistant material (18) in a mold, wherein the airfoil component (12) and the shroud heat resistant material (18) each comprises an interlocking feature (24); preheating the mold; introducing molten structural material (46) into the mold; and solidifying the molten structural material such that it interlocks the pre-formed airfoil component (12) with respect to the preformed shroud heat resistant material (18) and is effective to provide structural support for the shroud heat resistant material (18). Surfaces between the airfoil component (12) and the structural material (46), between the airfoil component (12) and the shroud heat resistant material (18), and between the shroud heat resistant material (18) and the structural material (46) are free of metallurgical bonds.
摘要翻译：多部件叶片段及其形成方法。组件包括：将预先形成的翼型件（12）和预制的护罩耐热材料（18）定位在模具中，其中翼型件（12）和护罩耐热材料（18）各自包括互锁特征（24 ）; 预热模具; 将熔融结构材料（46）引入模具中; 并且使熔融的结构材料凝固，使得其相对于预成型的护罩耐热材料（18）将预先形成的翼型件（12）联锁起来，并有效地为护罩耐热材料（18）提供结构支撑。机翼部件（12）和结构材料（46）之间，翼型部件（12）和护罩耐热材料（18）之间以及护罩耐热材料（18）和结构材料（46）之间的表面没有冶金债券。

47. 发明授权

US07950146B2 Co-forged steel rotor component for steam and gas turbine engines 有权
标题翻译：用于蒸汽和燃气涡轮发动机的共锻钢转子部件
公开(公告)号：US07950146B2
公开(公告)日：2011-05-31
申请号：US11784988
申请日：2007-04-10
申请人： Douglas J. Arrell , Allister W. James
发明人： Douglas J. Arrell , Allister W. James
IPC分类号： F01D5/02 , F01D5/34
CPC分类号： B23P15/006 , B21J1/00 , B21K1/32 , B21K3/00 , F01D5/02 , Y10T29/4932 , Y10T29/49321
摘要： A method of forming a rotor for a turbine engine such that the rotor is formed of two materials including: an outer ring formed from a first steel material, and a disk formed from a second material, such as a low alloy steel, having a larger thermal expansion coefficient than the first material forming the inner disk. The ring may include an inner aperture having a conical shape, and the disk may have an outer surface with a conical shape and a diameter with a portion that is larger than a portion of the ring. The ring may be heated such that the aperture expands to a size greater than the largest diameter of the inner disk. The ring may be positioned over the disk and allowed to cool to allow the ring to be attached to the disk. The ring and disk may then be co-forged.
摘要翻译：一种形成涡轮发动机的转子的方法，使得转子由两种材料形成，包括：由第一钢材形成的外圈和由诸如低合金钢的第二材料形成的盘，其具有较大的热膨胀系数比形成内盘的第一种材料高。环可以包括具有圆锥形状的内孔，并且盘可以具有圆锥形的外表面和具有大于环的一部分的部分的直径。可以加热环，使得孔扩大到比内盘最大直径大的尺寸。环可以定位在盘上并允许冷却以允许环附接到盘。然后可以共同锻造环和盘。

48. 发明授权

US07854809B2 Heat treatment system for a composite turbine engine component 有权
标题翻译：用于复合涡轮发动机部件的热处理系统
公开(公告)号：US07854809B2
公开(公告)日：2010-12-21
申请号：US11784985
申请日：2007-04-10
申请人： Douglas J. Arrell , Allister W. James
发明人： Douglas J. Arrell , Allister W. James
IPC分类号： C21D8/02 , C21D6/02
CPC分类号： C21D1/22 , C21D1/58 , C21D1/613 , C21D6/02 , C22F1/10
摘要： A heat treatment process for a component of a turbine engine formed from multiple materials, such as steel and nickel. The heat treatment process includes two stages: a first stage for austinitizing the steel and solutioning the nickel, and a second stage for ageing and tempering the materials. The heat treatment process may include heating a component formed from a steel portion and a nickel portion such that the steel portion austinitizes and the nickel portion undergoes solutioning, cooling the component to prevent the excessive formation of gamma prime ({grave over (y)}), and subjecting the component to a temper heat treatment during which martensite tempering occurs.
摘要翻译：一种用于由诸如钢和镍的多种材料形成的涡轮发动机的部件的热处理方法。热处理工艺包括两个阶段：用于奥氏体化钢和溶解镍的第一阶段，以及用于老化和回火材料的第二阶段。热处理方法可以包括加热由钢部分和镍部分形成的部件，使得钢部分奥氏体化，并且镍部分进行溶解，冷却该部件以防止过大的γ'（（（y）} ），对该部件进行马氏体回火的回火热处理。

49. 发明申请

US20090183850A1 Method of Making a Combustion Turbine Component from Metallic Combustion Turbine Subcomponent Greenbodies 审中-公开
标题翻译：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。

50. 发明授权

US09156086B2 Multi-component assembly casting 有权
标题翻译：多组件组装铸造
公开(公告)号：US09156086B2
公开(公告)日：2015-10-13
申请号：US12795002
申请日：2010-06-07
申请人： Allister W. James
发明人： Allister W. James
IPC分类号： F01D5/18 , B22D19/00 , B22C9/04 , C22C19/03 , F01D5/14 , F01D5/28
CPC分类号： B22D19/00 , B22C9/04 , C22C19/03 , F01D5/147 , F01D5/187 , F01D5/28 , F05D2230/211 , F05D2300/607 , Y10T29/4932 , Y10T29/49341
摘要： Multi-component vane segment and method for forming the same. Assembly includes: positioning a pre-formed airfoil component (12) and a preformed shroud heat resistant material (18) in a mold, wherein the airfoil component (12) and the shroud heat resistant material (18) each comprises an interlocking feature (24); preheating the mold; introducing molten structural material (46) into the mold; and solidifying the molten structural material such that it interlocks the pre-formed airfoil component (12) with respect to the preformed shroud heat resistant material (18) and is effective to provide structural support for the shroud heat resistant material (18). Surfaces between the airfoil component (12) and the structural material (46), between the airfoil component (12) and the shroud heat resistant material (18), and between the shroud heat resistant material (18) and the structural material (46) are free of metallurgical bonds.
摘要翻译：多部件叶片段及其形成方法。组件包括：将预先形成的翼型件（12）和预制的护罩耐热材料（18）定位在模具中，其中翼型件（12）和护罩耐热材料（18）各自包括互锁特征（24 ）; 预热模具; 将熔融结构材料（46）引入模具中; 并且使熔融的结构材料凝固，使得其相对于预成型的护罩耐热材料（18）将预先形成的翼型件（12）联锁起来，并有效地为护罩耐热材料（18）提供结构支撑。机翼部件（12）和结构材料（46）之间，翼型部件（12）和护罩耐热材料（18）之间以及护罩耐热材料（18）和结构材料（46）之间的表面没有冶金债券。

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