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    Method of Making a Combustion Turbine Component Having a Plurality of Surface Cooling Features and Associated Components
    1.
    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。

    Method of Making a Combustion Turbine Component Having a Plurality of Surface Cooling Features and Associated Components
    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：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。

    Patterned reduction of surface area for abradability
    5.
    发明授权
    Patterned reduction of surface area for abradability 有权
    图形化的表面积减少磨损性

    公开(公告)号：US09297269B2

    公开(公告)日：2016-03-29

    申请号：US11800801

    申请日：2007-05-07

    申请人： Jay A. Morrison ,  Jay E. Lane ,  Gary B. Merrill

    发明人： Jay A. Morrison ,  Jay E. Lane ,  Gary B. Merrill

    IPC分类号： B32B3/30 ,  F01D11/12

    CPC分类号： F01D11/122 ,  B32B3/30 ,  F05D2250/18 ,  F05D2250/70 ,  F05D2300/21 ,  F05D2300/603 ,  Y10T428/24355

    摘要： A gas turbine component (20) with a layer of ceramic material (22) defining a wear surface (21), in which an array of cross-shaped depressions (26A, 26B) formed in the wear surface (21) define a continuous labyrinth of orthogonal walls (28, 30) of the ceramic material, and reduce the area of the wear surface (21) by about 50%. Within a representative area (36) of the wear surface (21), the depressions (26A, 26B) provide a ratio of a lineal sum of depression perimeters (27) divided by the representative area (36) of the wear surface of least 0.9 per unit of measurement for improved abradability characteristics of the wear surface (21).

    摘要翻译： 一种具有限定磨损表面（21）的陶瓷材料层（22）的燃气轮机部件（20），其中形成在磨损表面（21）中的十字形凹陷阵列（26A，26B）限定了连续的迷宫 的陶瓷材料的正交壁（28,30），并且将磨损表面（21）的面积减小约50％。 在磨损表面（21）的代表区域（36）内，凹陷（26A，26B）提供凹陷周长（27）的直线和除以磨损表面的代表区域（36）的比率为至少0.9 每单位测量以改善磨损表面（21）的耐磨特性。

    Method of joining ceramic parts and articles so formed
    6.
    发明授权
    Method of joining ceramic parts and articles so formed 有权
    陶瓷部件和如此形成的制品的接合方法

    公开(公告)号：US09068464B2

    公开(公告)日：2015-06-30

    申请号：US11188406

    申请日：2005-07-25

    申请人： Jay A. Morrison ,  Jay E. Lane ,  Gary B. Merrill

    发明人： Jay A. Morrison ,  Jay E. Lane ,  Gary B. Merrill

    IPC分类号： B21D53/78 ,  F01D5/28 ,  B23P15/04 ,  F01D9/04

    CPC分类号： F01D5/282 ,  B23P15/04 ,  C04B37/001 ,  C04B37/005 ,  C04B2237/341 ,  C04B2237/343 ,  C04B2237/365 ,  C04B2237/38 ,  C04B2237/76 ,  C04B2237/84 ,  F01D5/284 ,  F01D9/044 ,  F05D2230/23 ,  F05D2240/30 ,  Y10T29/49337 ,  Y10T29/49552

    摘要： A method for joining a first CMC part (30) having an outer joining portion (32), and a second CMC part (36) having an inner joining portion (38). The second CMC part (36) is heat-cured to a stage of shrinkage more complete than that of the first CMC part (30) prior to joining. The two CMC parts (30, 36) are joined in a mating interface that captures the inner joining portion (38) within the outer joining portion (32). The assembled parts (30, 36) are then fired together, resulting in differential shrinkage that compresses the outer joining portion (32) onto the inner joining portion (38), providing a tightly pre-stressed joint. Optionally, a refractory adhesive (42) may be used in the joint. Shrinkage of the outer joining portion (32) avoids shrinkage cracks in the adhesive (42).

    摘要翻译： 一种用于接合具有外接合部分（32）的第一CMC部件（30）和具有内接合部分（38）的第二CMC部件（36）的方法。 第二CMC部分（36）在接合之前被热固化到比第一CMC部分（30）的收缩阶段更完整的阶段。 两个CMC部件（30,36）连接在捕获外接合部分（32）内的内接合部分（38）的配合接口中。 然后将组装好的部件（30,36）烧结在一起，导致不均匀的收缩，将外部接合部分（32）压缩到内部接合部分（38）上，从而提供紧密的预应力接头。 可选地，可以在接头中使用耐火粘合剂（42）。 外接合部分（32）的收缩避免了粘合剂（42）中的收缩裂纹。

    Patterned reduction of surface area for abradability
    8.
    发明申请
    Patterned reduction of surface area for abradability 有权
    图形化的表面积减少磨损性

    公开(公告)号：US20080280101A1

    公开(公告)日：2008-11-13

    申请号：US11800801

    申请日：2007-05-07

    申请人： Jay A. Morrison ,  Jay E. Lane ,  Gary B. Merrill

    发明人： Jay A. Morrison ,  Jay E. Lane ,  Gary B. Merrill

    IPC分类号： B32B3/30

    CPC分类号： F01D11/122 ,  B32B3/30 ,  F05D2250/18 ,  F05D2250/70 ,  F05D2300/21 ,  F05D2300/603 ,  Y10T428/24355

    摘要： A gas turbine component (20) with a layer of ceramic material (22) defining a wear surface (21), in which an array of cross-shaped depressions (26A, 26B) formed in the wear surface (21) define a continuous labyrinth of orthogonal walls (28, 30) of the ceramic material, and reduce the area of the wear surface (21) by about 50%. Within a representative area (36) of the wear surface (21), the depressions (26A, 26B) provide a ratio of a lineal sum of depression perimeters (27) divided by the representative area (36) of the wear surface of least 0.9 per unit of measurement for improved abradability characteristics of the wear surface (21).

    摘要翻译： 具有限定磨损表面（21）的陶瓷材料层（22）的燃气轮机部件（20），其中形成在磨损表面（21）中的十字形凹陷（26A，26B）阵列限定了一个 陶瓷材料的正交壁（28,30）的连续迷宫，并且将磨损表面（21）的面积减小约50％。 在磨损表面（21）的代表性区域（36）内，凹陷（26A，26B）提供凹陷周长（27）的直线和除以磨损表面的代表区域（36） 每单位测量值最小为0.9，以改善磨损表面（21）的磨损性能。