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1.发明公开Ceramic matrix composite airfoil segment for a gas turbine engine, corresponding structure and method of assembling 审中-公开陶瓷纤维复合材料的叶片区段一种用于燃气涡轮发动机相关联的结构和组装过程
公开(公告)号：EP2570593A2
公开(公告)日：2013-03-20
申请号：EP12169245.3
申请日：2012-05-24
发明人： Berczik, Douglas M. , Suciu, Gabriel L. , Merry, Brian D. , Alvanos, Ioannis , Dye, Christopher M.
CPC分类号： F01D5/282 , C04B37/00 , C04B2235/5244 , C04B2237/365 , C04B2237/38 , C04B2237/76 , F01D5/147 , F01D5/284 , F01D9/041 , F01D25/246 , F05D2240/12 , F05D2300/6033 , Y10T29/49321
摘要： A ceramic matrix composite (CMC) airfoil segment (82) for a gas turbine engine (20) includes a box-shape fiber geometry (98A) which defines a rectilinear pressure side bond line (100P) and a rectilinear suction side bond line (100S). A corresponding structure and method of assembling are also provided.
摘要翻译： 一种用于燃气涡轮发动机（20）一种陶瓷基复合材料（CMC）的翼型部段（82）包括箱形光纤几何结构（98A），其限定了直线压力侧粘合线（100P）和直线吸力侧粘合线（100S ）。 因此，提供一个相应的结构和组装方法。
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公开(公告)号：EP1209248A2
公开(公告)日：2002-05-29
申请号：EP02001996.4
申请日：1995-02-15
CPC分类号： C23C14/32 , C23C14/16 , C23C14/325 , C23C30/00 , Y10S428/938 , Y10T428/12806 , Y10T428/12903
摘要： An oxidation resistant structure is taught comprising a Ti alloy substrate and a uniform coating of a Cu alloy deposited on the substrate, wherein the Cu alloy comprises Cu and from 0 to 10 wt% Al and from 0 to 6 wt% Si and the percentages of Al and Si are not simultaneously zero, the structure having substantially no intermetallic compound formation and substantially no diffusion of coating constituents in the substrate.
摘要翻译： 教导了一种抗氧化结构，其包含Ti合金基底和沉积在基底上的Cu合金的均匀涂层，其中Cu合金包含Cu和0-10重量％的Al和0-6重量％的Si，并且 Al和Si不同时为零，该结构基本上没有形成金属间化合物，基本上没有涂层组分在衬底中的扩散。
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公开(公告)号：EP2450127A3
公开(公告)日：2016-07-13
申请号：EP11187817.9
申请日：2011-11-04
发明人： Bochiechio, Mario P. , Castle, Lea Kennard , Beers, Russell A. , Bartholomew, Mark F. , Berczik, Douglas M.
IPC分类号： B22D17/22
CPC分类号： B22D17/2209
摘要： A high temperature die casting system (10) includes a die casting tool (12) that has dies (14,16) that are adapted for forming a component (15). The die casting tool (12) is operable to heat and maintain a temperature of the dies (14,16) above 500°F (260°C). At least a portion of the die casting tool (12) that is exposed for contact with molten die casting material has a substrate (42) and barrier coating (40) on the substrate (42) to protect from the molten die casting material.
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4.发明公开Die casting system and method utilizing high melting temperature materials 审中-公开压铸系统和方法，用于使用材料具有高的熔化温度
公开(公告)号：EP2450126A2
公开(公告)日：2012-05-09
申请号：EP11187963.1
申请日：2011-11-04
发明人： Bochiechio, Mario P. , Shah, Dilip M. , Castle, Lea Kennard , Berczik, Douglas M. , Marcin, John Joseph , Verner, Carl R.
CPC分类号： B22D17/2023 , B22D17/2209
摘要： A die casting system (50) includes a die (52) comprising of a plurality of die components (54, 56) that define a die cavity (60) configured to receive a molten metal. One of the die components (54, 56) comprises a material that is not reactive with the molten metal and has a melting temperature above 815 degrees Celsius.
摘要翻译： 的压铸系统（50）包括一对（52）包括以下部件（54，56）的多元定义一个没经配置以接收熔融金属的腔（60）。 一项所述的组件（54，56）包括一材料所做的是不与熔融金属反应，并具有的熔融温度以上摄氏815度。
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公开(公告)号：EP2450127B1
公开(公告)日：2019-10-09
申请号：EP11187817.9
申请日：2011-11-04
发明人： Bochiechio, Mario P. , Castle, Lea Kennard , Beers, Russell A. , Bartholomew, Mark F. , Berczik, Douglas M.
IPC分类号： B22D17/22
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6.发明授权
公开(公告)号：EP2570611B1
公开(公告)日：2019-02-20
申请号：EP12169258.6
申请日：2012-05-24
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7.发明公开Ceramic matrix composite airfoil for a gas turbine engine and corresponding method of forming 审中-公开Schaufelprofil aus keramischem Faserverbundwerkstofffürein Gasturbinentriebwerk undzugehörigesFormungsverfahren
公开(公告)号：EP2570611A2
公开(公告)日：2013-03-20
申请号：EP12169258.6
申请日：2012-05-24
CPC分类号： F01D5/284 , F01D5/282 , F01D5/34 , F01D9/041 , F01D11/001 , F01D25/246 , F05D2240/12 , F05D2300/6033
摘要： A ceramic matrix composite (CMC) airfoil (66) for a gas turbine engine (20) includes a first multiple of CMC plies (88) which define a suction side (84), a first airfoil portion (88A) of the first multiple of CMC plies (88) at least partially parallel to an airfoil axis (B). A second multiple of CMC plies (86) define a pressure side (82), a second airfoil portion (86A) of the second multiple of CMC plies (86) at least partially parallel to the airfoil axis (B) and bonded to the first airfoil portion (88A). A corresponding method of forming is also provided.
摘要翻译： 一种用于燃气涡轮发动机（20）的陶瓷基体复合材料（CMC）翼型件（66）包括限定吸力侧（84）的CMC层（88）的第一倍数，第一翼型部分（88A） CMC层（88）至少部分平行于翼型轴线（B）。 CMC层（86）的第二倍数限定压力侧（82），至少部分平行于翼型轴线（B）的CMC层（86）的第二多个（86）的第二翼型部分（86A）并且结合到第一 机翼部分（88A）。 还提供了相应的成型方法。
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8.发明公开Bond coating and thermal barrier compositions, processes for applying both, and their coated articles 有权Haftbeschichtungs-和热坝组合物，同时使用的方法，并用两者涂覆制品
公开(公告)号：EP1842937A2
公开(公告)日：2007-10-10
申请号：EP07250080.4
申请日：2007-01-09
CPC分类号： C04B35/58092 , C04B2235/3873 , C04B2235/96 , C22C27/04 , C23C4/04 , C23C4/06 , C23C26/00 , C23C28/324 , C23C28/3455 , C23C28/36 , Y10T428/12021 , Y10T428/12458 , Y10T428/249961 , Y10T428/26 , Y10T428/265
摘要： A coated article includes an article (30) having at least one surface and composed of a molybdenum based refractory metal alloy base substrate, a niobium based refractory metal alloy base substrate or a silicon base substrate. A bond coat layer (32) is disposed upon the surface. The bond coat layer (32) includes a molybdenum disilicide base compound and at least one of the following: silicon nitride, silicon carbide or tantalum oxide. A process for coating the article includes the steps of applying upon the article's surface the aforementioned bond coat layer (32). A functionally graded material layer (34) is applied upon the bond coat layer (32). The functionally graded material layer (34) comprises molybdenum disilicide, mullite and at least one of the following: silicon nitride, silicon carbide or tantalum oxide. A thermal barrier coating layer (36) is then applied upon the functionally graded material layer (34).
摘要翻译： 一种涂覆制品包括在制品（30），其具有至少一个表面和基于钼的难熔金属合金基材基片组成的，一个基于铌难熔金属合金基底基板或硅基基体。 的粘合涂层（32）在所述表面布置。 粘合涂层（32）包括二硅化钼基化合物和以下中的至少一个：氮化硅，碳化硅或氧化钽。 一种用于涂覆物品的过程包括施加在制品的表面上的上述粘合涂层（32）的步骤。 功能梯度材料层（34）在所述粘合涂层（32）施加。 功能梯度材料层（34）包括二硅化钼，莫来石和以下中的至少一个：氮化硅，碳化硅或氧化钽。 热障涂层（36），然后在所述功能梯度材料层（34）中的应用。
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9.发明公开Die casting system and method utilizing high melting temperature materials 审中-公开压铸系统和方法，用于使用材料具有高的熔化温度
公开(公告)号：EP2450126A3
公开(公告)日：2016-01-06
申请号：EP11187963.1
申请日：2011-11-04
发明人： Bochiechio, Mario P. , Shah, Dilip M. , Castle, Lea Kennard , Berczik, Douglas M. , Marcin, John Joseph , Verner, Carl R.
CPC分类号： B22D17/2023 , B22D17/2209
摘要： A die casting system (50) includes a die (52) comprising of a plurality of die components (54, 56) that define a die cavity (60) configured to receive a molten metal. One of the die components (54, 56) comprises a material that is not reactive with the molten metal and has a melting temperature above 815 degrees Celsius.
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10.发明公开Ceramic matrix composite airfoil segment for a gas turbine engine, corresponding structure and method of assembling 审中-公开陶瓷纤维复合材料的叶片区段一种用于燃气涡轮发动机相关联的结构和组装过程
公开(公告)号：EP2570593A3
公开(公告)日：2015-08-12
申请号：EP12169245.3
申请日：2012-05-24
发明人： Berczik, Douglas M. , Suciu, Gabriel L. , Merry, Brian D. , Alvanos, Ioannis , Dye, Christopher M.
CPC分类号： F01D5/282 , C04B37/00 , C04B2235/5244 , C04B2237/365 , C04B2237/38 , C04B2237/76 , F01D5/147 , F01D5/284 , F01D9/041 , F01D25/246 , F05D2240/12 , F05D2300/6033 , Y10T29/49321
摘要： A ceramic matrix composite (CMC) airfoil segment (82) for a gas turbine engine (20) includes a box-shape fiber geometry (98A) which defines a rectilinear pressure side bond line (100P) and a rectilinear suction side bond line (100S). A corresponding structure and method of assembling are also provided.
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