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1.发明授权Abradable composition, a method of manufacturing an abradable composition and a gas turbine engine having an abradable seal 失效可磨性组合物，可磨性组合物的制造方法和具有耐磨性密封件的燃气轮机
公开(公告)号：US5962076A
公开(公告)日：1999-10-05
申请号：US064143
申请日：1998-04-22
IPC分类号： F01D11/08 , B32B18/00 , C04B20/00 , C04B28/34 , C09K3/10 , F01D11/12 , F16J15/20 , C04B35/447 , B32B5/16 , C04B35/78 , F01D11/00
CPC分类号： B32B18/00 , C04B20/002 , C04B28/34 , F01D11/127 , B22F2003/1106 , C04B2111/00353 , C04B2111/00612 , C04B2235/656 , C04B2235/6567 , C04B2235/661 , C04B2237/34 , C04B2237/341 , C04B2237/343 , C04B2237/38 , Y10T428/252 , Y10T428/256 , Y10T428/259 , Y10T428/2982
摘要： An abradable seal comprises a plurality of hollow aluminosilicate spheres in a matrix of aluminium phosphate. The matrix of aluminium phosphate also has an aluminosilicate filler. The hollow aluminosilicate spheres have a diameter in the range of 400 to 1800 microns, preferably a diameter in the range of 800 to 1400 microns. The weight proportion of hollow aluminosilicate spheres in the abradable seal is 30% to 50%. The density of the abradable seal is 1.5 grams per cubic centimeter. The hollow aluminosilicate spheres in the aluminium phosphate matrix have a relatively high temperature capability of approximately 1300.degree. C. maximum. This makes the abradable seal better able to withstand the environment in the turbine of a turbofan gas turbine engine.
摘要翻译： 可磨损密封件包括在磷酸铝基质中的多个中空铝硅酸盐球体。 磷酸铝基质也具有铝硅酸盐填料。 中空铝硅酸盐球体的直径在400至1800微米的范围内，优选直径在800至1400微米的范围内。 耐磨密封件中的中空铝硅酸盐球的重量比例为30％至50％。 耐磨密封件的密度为1.5克/立方厘米。 磷酸铝基体中的中空铝硅酸盐球体具有最高约1300℃的较高温度能力。 这使得可磨损密封件更好地能够承受涡轮风扇燃气涡轮发动机的涡轮机中的环境。
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2.发明授权Abradable composition, a method of manufacturing an abradable composition and a gas turbine engine having an abradable seal 失效可磨性组合物，可磨性组合物的制造方法和具有耐磨性密封件的燃气轮机
公开(公告)号：US5780146A
公开(公告)日：1998-07-14
申请号：US651486
申请日：1996-05-22
IPC分类号： F01D11/08 , B32B18/00 , C04B20/00 , C04B28/34 , C09K3/10 , F01D11/12 , F16J15/20 , C04B35/447 , B32B5/16 , C04B35/78 , F01D11/00
CPC分类号： B32B18/00 , C04B20/002 , C04B28/34 , F01D11/127 , B22F2003/1106 , C04B2111/00353 , C04B2111/00612 , C04B2235/656 , C04B2235/6567 , C04B2235/661 , C04B2237/34 , C04B2237/341 , C04B2237/343 , C04B2237/38 , Y10T428/252 , Y10T428/256 , Y10T428/259 , Y10T428/2982
摘要： An abradable seal comprises a plurality of hollow aluminosilicate spheres in a matrix of aluminium phosphate. The matrix of aluminium phosphate also has an aluminosilicate filler. The hollow aluminosilicate spheres have a diameter in the range of 400 to 1800 microns, preferably a diameter in the range of 800 to 1400 microns. The weight proportion of hollow aluminosilicate spheres in the abradable seal is 30% to 50%. The density of the abradable seal is 1.5 grammes per cubic centimetre. The hollow aluminosilicate spheres in the aluminium phosphate matrix have a relatively high temperature capability of approximately 1300.degree. C. maximum. This makes the abradable seal better able to withstand the environment in the turbine of a turbofan gas turbine engine.
摘要翻译： 可磨损密封件包括在磷酸铝基质中的多个中空铝硅酸盐球体。 磷酸铝基质也具有铝硅酸盐填料。 中空铝硅酸盐球体的直径在400至1800微米的范围内，优选直径在800至1400微米的范围内。 耐磨密封件中的中空铝硅酸盐球的重量比例为30％至50％。 耐磨密封件的密度为1.5克/立方厘米。 磷酸铝基体中的中空铝硅酸盐球体具有最高约1300℃的较高温度能力。 这使得可磨损密封件更好地能够承受涡轮风扇燃气涡轮发动机的涡轮机中的环境。
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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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公开(公告)号：US08813812B2
公开(公告)日：2014-08-26
申请号：US13974651
申请日：2013-08-23
申请人： Ahmed Kamel , Gary B. Merrill
发明人： Ahmed Kamel , Gary B. Merrill
IPC分类号： B22C9/10
CPC分类号： B22C9/103
摘要： A hollow turbine engine component with complex internal features can include a first region and a second, high resolution region. The first region can be defined by a first ceramic core piece formed by any conventional process, such as by injection molding or transfer molding. The second region can be defined by a second ceramic core piece formed separately by a method effective to produce high resolution features, such as tomo lithographic molding. The first core piece and the second core piece can be joined by interlocking engagement that once subjected to an intermediate thermal heat treatment process thermally deform to form a three dimensional interlocking joint between the first and second core pieces by allowing thermal creep to irreversibly interlock the first and second core pieces together such that the joint becomes physically locked together providing joint stability through thermal processing.
摘要翻译： 具有复杂内部特征的中空涡轮发动机部件可以包括第一区域和第二高分辨率区域。 第一区域可以由通过任何常规方法形成的第一陶瓷芯片来定义，例如通过注塑或传递模塑。 第二区域可以由通过有效产生高分辨率特征的方法分开形成的第二陶瓷芯片来定义，例如层压平版印刷。 第一芯片和第二芯片可以通过互锁配合连接在一起，一旦中间热处理工艺进行了热变形，热变形就可以通过使热蠕变不可逆地互锁在第一和第二芯片之间而形成三维互锁接头 和第二芯片在一起，使得接头物理锁定在一起，通过热处理提供接头稳定性。
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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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公开(公告)号：US08764394B2
公开(公告)日：2014-07-01
申请号：US12985553
申请日：2011-01-06
CPC分类号： F01D5/18 , F01D5/187 , F05D2240/304 , F05D2250/13 , F05D2260/2214 , F28F3/048 , F28F7/02
摘要： A cooling channel (36, 36B) cools an exterior surface (40 or 42) or two opposed exterior surfaces (40 and 42). The channel has a near-wall inner surface (48, 50) with a width (W1). Interior side surfaces (52, 54) may converge to a reduced channel width (W2). The near-wall inner surface (48, 50) may have fins (44) aligned with a coolant flow (22). The fins may highest at mid-width of the near-wall inner surface. A two-sided cooling channel (36) may have two near-wall inner surfaces (48, 50) parallel to two respective exterior surfaces (40, 42), and may have an hourglass shaped transverse sectional profile. The tapered channel width (W1, W2) and the fin height profile (56A, 56B) increases cooling flow (22) into the corners (C) of the channel for more uniform and efficient cooling.
摘要翻译： 冷却通道（36,36B）冷却外表面（40或42）或两个相对的外表面（40和42）。 通道具有宽度（W1）的近壁内表面（48,50）。 内侧表面（52,54）可以会聚到减小的通道宽度（W2）。 近壁内表面（48,50）可以具有与冷却剂流（22）对准的翅片（44）。 翅片在近壁内表面的中间宽度处可能最高。 双面冷却通道（36）可以具有两个平行于两个相应的外表面（40,42）的近壁内表面（48,50），并且可以具有沙漏形横截面轮廓。 锥形通道宽度（W1，W2）和翅片高度轮廓（56A，56B）将冷却流（22）增加到通道的拐角（C），以实现更均匀和有效的冷却。
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公开(公告)号：US20120285652A1
公开(公告)日：2012-11-15
申请号：US13103338
申请日：2011-05-09
申请人： Fathi Ahmad , Gary B. Merrill , Uwe Paul
发明人： Fathi Ahmad , Gary B. Merrill , Uwe Paul
CPC分类号： B22D17/22 , B22C7/02 , B22C9/06 , B29C33/68 , B29C67/241
摘要： A liner for a die body is presented. The liner includes a flexible base material characterized in that reinforcements with lower stretchability compared to the base material are bonded along the extent of the liner. A tool which includes the liner is also provided. The reinforcements may include glass fibers or carbon fibers.
摘要翻译： 提出了一种用于模具主体的衬垫。 衬套包括柔性基体材料，其特征在于，与基底材料相比，具有较低拉伸性的增强材料沿衬垫的程度粘合。 还提供了包括衬套的工具。 加强件可以包括玻璃纤维或碳纤维。
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8.发明授权公开(公告)号：US08247062B2
公开(公告)日：2012-08-21
申请号：US12464543
申请日：2009-05-12
申请人： Jay A. Morrison , Gary B. Merrill
发明人： Jay A. Morrison , Gary B. Merrill
CPC分类号： C04B35/80 , B32B18/00 , C04B2235/945 , C04B2237/38 , C04B2237/64 , Y10T156/1039 , Y10T156/1044 , Y10T428/24124 , Y10T428/24132 , Y10T428/24479 , Y10T428/24529 , Y10T428/249928
摘要： Methodology and tooling arrangements for increasing interlaminar shear strength in a ceramic matrix composite (CMC) structure are provided. The CMC structure may be formed by a plurality of layers of ceramic fibers disposed between a top surface and a bottom surface of the composite structure. A plurality of surface recesses are formed on the surfaces of the structure. For example, each of the surfaces of the composite structure may be urged against corresponding top and bottom surfaces of a tool having a plurality of asperities. The plurality of surface recesses causes an out-of-plane sub-surface fiber displacement along an entire thickness of the structure, and the sub-surface fiber displacement is arranged to increase an interlaminar shear strength of the structure.
摘要翻译： 提供了用于增加陶瓷基体复合材料（CMC）结构中的层间剪切强度的方法和工具布置。 CMC结构可以由布置在复合结构的顶表面和底表面之间的多层陶瓷纤维形成。 在结构的表面上形成多个表面凹部。 例如，复合结构的每个表面可以被推压到具有多个凹凸的工具的相应的顶部和底部表面上。 所述多个表面凹部沿着所述结构的整个厚度引起面外亚表面纤维位移，并且所述次表面纤维位移被布置成增加所述结构的层间剪切强度。
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公开(公告)号：US20100251721A1
公开(公告)日：2010-10-07
申请号：US11784154
申请日：2007-04-05
CPC分类号： F01D5/147 , F01D5/282 , F05D2300/603
摘要： A stacked laminate component for a turbine engine that may be used as a replacement for one or more metal components is provided. The stacked laminate component can have a body formed by a process of stacking and laminating layers to define a radially inner surface along the hot gas path. The layers can be substantially orthogonal to the radially inner surface. The layers can be at least a first layer of a first material and a second layer of a second material. At least the first material is a ceramic matrix composite. The second material can have a higher thermal conductivity or a higher creep strength than the first material.
摘要翻译： 提供了可用作一种或多种金属部件的替代物的用于涡轮发动机的堆叠层叠部件。 堆叠的层叠部件可以具有通过堆叠和层压层以形成沿着热气体路径的径向内表面的过程形成的主体。 这些层可以基本上垂直于径向内表面。 这些层可以是至少第一材料的第一层和第二材料的第二层。 至少第一种材料是陶瓷基复合材料。 第二材料可以具有比第一材料更高的导热性或更高的蠕变强度。
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公开(公告)号：US07686577B2
公开(公告)日：2010-03-30
申请号：US11591907
申请日：2006-11-02
申请人： Jay A. Morrison , David C. Radonovich , Anthony L. Schiavo , Gary B. Merrill , Malberto F. Gonzalez
发明人： Jay A. Morrison , David C. Radonovich , Anthony L. Schiavo , Gary B. Merrill , Malberto F. Gonzalez
IPC分类号： F01D25/26
CPC分类号： F01D11/08 , F01D9/04 , F05D2240/11 , F05D2300/603 , Y10T29/49888
摘要： A ceramic ring segment for a turbine engine that may be used as a replacement for one or more metal components. The ceramic ring segment may be formed from a plurality of ceramic plates, such as ceramic matrix composite plates, that are joined together using a strengthening mechanism to reinforce the ceramic plates while permitting the resulting ceramic article to be used as a replacement for components for turbine systems that are typically metal, thereby taking advantage of the properties provided by ceramic materials. The strengthening mechanism may include a ceramic matrix composite overwrap or plurality of overwraps designed to help prevent delamination of the ceramic plates when the ceramic article is in use by placing the plates in compression.
摘要翻译： 用于涡轮发动机的陶瓷环段，其可用作一种或多种金属组分的替代物。 陶瓷环段可以由多个陶瓷板形成，例如陶瓷基复合板，其使用强化机构连接在一起以加强陶瓷板，同时允许所得的陶瓷制品用作涡轮机部件的替代品 通常是金属的系统，从而利用由陶瓷材料提供的性质。 加强机构可以包括陶瓷基复合材料外包装或多个外包装，其被设计成当陶瓷制品在使用时通过将板放置在压缩中来帮助防止陶瓷板的分层。
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