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1.发明申请HYBRID MANUFACTURING PROCESS AND PRODUCT MADE USING LAMINATED SHEETS AND COMPRESSIVE CASING 有权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
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。
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2.发明申请JOINING MECHANISM AND METHOD FOR INTERLOCKING MODULAR TURBINE ENGINE COMPONENT WITH A SPLIT RING 有权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
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）。
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公开(公告)号：US20110132562A1
公开(公告)日：2011-06-09
申请号：US12961621
申请日：2010-12-07
摘要： Alloy products are produced with a waxless casting process. A model of a ceramic casting vessel (34) defining a desired product shape is digitally divided into sections (10, 40, 42). Each section is translated into a soft alloy mater tool (14) including precision inserts (20) where needed for fine detail. A flexible mold (24) is cast from each master tool, and a section of the ceramic casting vessel is cast from the respective flexible mold. The vessel sections are assembled by aligning cooperating precision features (58, 60) cast directly into each section and the alloy part is cast therein. No wax or wax pattern tooling is needed to produce the cast alloy product. Engineered surface features (54) may be included on both the interior and exterior surfaces of the shell sections.
摘要翻译： 合金产品采用无蜡铸造工艺生产。 限定期望产品形状的陶瓷铸造容器（34）的模型被数字地分成部分（10,40,42）。 每个部分被翻译成软合金工具（14），其包括精确插入件（20），其中需要精细的细节。 从每个主工具铸造柔性模具（24），并且从相应的柔性模具铸造一部分陶瓷铸造容器。 通过对准协调的精确特征（58,60）直接铸造到每个部分中并且合金部件被浇铸在其中来组装容器部分。 不需要蜡或蜡图案模具来生产铸造合金产品。 工程表面特征（54）可以包括在壳部分的内表面和外表面上。
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公开(公告)号：US09272324B2
公开(公告)日：2016-03-01
申请号：US12961720
申请日：2010-12-07
摘要： An investment casting process for a hollow component such as a gas turbine blade utilizing a ceramic core (10) that is cast in a flexible mold (24) using a low pressure, vibration assisted casting process. The flexible mold is cast from a master tool (14) machined from soft metal using a relatively low precision machining process, with relatively higher precision surfaces being defined by a precision formed insert (22) incorporated into the master tool. A plurality of identical flexible molds may be formed from a single master tool in order to permit the production of ceramic cores at a desired rate with a desired degree of part-to-part precision.
摘要翻译： 一种用于中空部件的熔模铸造方法，所述中空部件例如是使用利用低压振动辅助铸造工艺铸造在柔性模具（24）中的陶瓷芯（10）的燃气轮机叶片。 柔性模具使用相对低精度的加工工艺从由软金属机加工的主工具（14）铸造，相对较高精度的表面由结合到主工具中的精密成型刀片（22）限定。 可以由单个主工具形成多个相同的柔性模具，以便允许以期望的速率以期望的部件到部件的精度制造陶瓷芯。
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5.发明授权Joining mechanism and method for interlocking modular turbine engine component with a split ring 有权用于将模块化涡轮发动机部件与分离环联动的联接机构和方法公开(公告)号：US08770930B2
公开(公告)日：2014-07-08
申请号：US13023721
申请日：2011-02-09
IPC分类号： F01D9/00
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）。
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6.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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公开(公告)号：US20110132564A1
公开(公告)日：2011-06-09
申请号：US12961740
申请日：2010-12-07
申请人： Gary B. Merrill , Allister W. James , Andrew J. Burns , Kevin C. Sheehan , Benjamin E. Heneveld , Iain A. Fraser
发明人： Gary B. Merrill , Allister W. James , Andrew J. Burns , Kevin C. Sheehan , Benjamin E. Heneveld , Iain A. Fraser
IPC分类号： B22C7/02
摘要： An investment casting process wherein the wax pattern tool (44) is flexible to facilitate removal of the tool from the cast wax pattern (52) even when the cast shape would otherwise require multiple pull planes. The flexible tool may include a flexible insert (42) precisely indexed to a surrounding coffin mold (40), and thereby to an enclosed ceramic core (10). Positioning pins (106) may extend from the flexible tool to make compliant contact against the core prior to a wax injection step. The surface of the resulting wax pattern may contain an engineered topography (36) replicated through the flexible surface from a master tool (12). The flexible tool may encase thermally conductive or magnetic particles (92), or other active device (96) such as a sensor or vibrator which is operable during wax injection.
摘要翻译： 一种熔模铸造工艺，其中蜡模工具（44）是柔性的，以便即使当铸造形状另外需要多个拉平面时，便于从铸蜡图案（52）中移除工具。 柔性工具可以包括精确地向周围的棺材模具（40）分度的柔性插入件（42），从而被封闭的陶瓷芯（10）。 定位销（106）可以从柔性工具延伸，以在蜡喷射步骤之前使其与芯部顺从接触。 所得蜡图案的表面可以包含通过主工具（12）通过柔性表面复制的工程化形貌（36）。 柔性工具可以包裹导热或磁性颗粒（92）或其它有效装置（96），例如在蜡注射期间可操作的传感器或振动器。
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8.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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9.发明授权公开(公告)号：US09206983B2
公开(公告)日：2015-12-08
申请号：US13096128
申请日：2011-04-28
申请人： Gary B. Merrill , Iain A. Fraser
发明人： Gary B. Merrill , Iain A. Fraser
CPC分类号： F23R3/002 , F23M5/08 , F23M2900/05004 , F23R3/06 , F23R2900/03041 , F23R2900/03042
摘要： A hot gas path component (100) including: a metallic substrate (102) disposed beneath an outer surface (112) of the component (100) that is exposed to a hot gas present during operation of an internal combustion engine; a thermal barrier coating (TBC) (110) disposed on the metallic substrate (102) and defining a first portion (118) of the component outer surface (112); and a powder metallurgy structure (104) bonded to the metallic substrate (102) and in contact with the TBC (110).
摘要翻译： 一种热气路径部件（100），包括：金属基板（102），其设置在所述部件（100）的外表面（112）的下方，所述外表面暴露于内燃机的运转期间存在的热气体; 设置在所述金属基板（102）上并限定所述部件外表面（112）的第一部分（118）的热障涂层（TBC）（110）; 和结合到金属基底（102）并与TBC（110）接触的粉末冶金结构（104）。
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10.发明授权Hybrid manufacturing process and product made using laminated sheets and compressive casing 有权混合制造工艺和使用层压板和压缩套管制成的产品公开(公告)号：US08940114B2
公开(公告)日：2015-01-27
申请号：US13094985
申请日：2011-04-27
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。
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