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公开(公告)号：US20170059165A1
公开(公告)日：2017-03-02
申请号：US14839260
申请日：2015-08-28
Applicant: Rolls-Royce High Temperature Composites Inc.
Inventor： Sujit Nanda
Abstract: A fluid conduit may be provided comprising a ceramic matrix composite (CMC) cross-over tube and a flange. The CMC cross-over tube may comprise a first end configured to extend into a first combustor liner of a gas turbine engine, and a second end configured to extend into a second combustor liner of a gas turbine engine. The interior of the CMC cross-over tube may define a passageway. The flange may extend outwardly from an outer surface of the CMC cross-over tube. The flange may be configured to engage at least one of the first combustor liner and the second combustor liner.
Abstract translation: 可以提供流体导管，其包括陶瓷基复合（CMC）交叉管和凸缘。 CMC交叉管可以包括构造成延伸到燃气涡轮发动机的第一燃烧器衬套中的第一端和构造成延伸到燃气涡轮发动机的第二燃烧器衬套中的第二端。 CMC交叉管的内部可以限定通道。 凸缘可以从CMC交叉管的外表面向外延伸。 凸缘可以被构造成接合第一燃烧器衬套和第二燃烧器衬套中的至少一个。
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公开(公告)号：US20170044070A1
公开(公告)日：2017-02-16
申请号：US15229786
申请日：2016-08-05
Inventor： Stephen I. Harris , Robert J. Shinavski , Sungbo Shim , Sean E. Landwehr
CPC classification number: C04B35/806 , C04B35/565 , C04B35/62857 , C04B35/6286 , C04B35/62863 , C04B35/62876 , C04B35/62884 , C04B35/62894 , C04B35/62897 , C04B37/005 , C04B37/006 , C04B2235/3826 , C04B2235/428 , C04B2235/5244 , C04B2235/614 , C04B2235/616 , C04B2237/08 , C04B2237/083 , C04B2237/122 , C04B2237/365 , C04B2237/38 , C04B2237/708 , C04B2237/72 , C23C16/045
Abstract: A ceramic matrix composite component and methods of making are described herein. The ceramic matrix composite may include a silicon containing matrix and refractory fibers embedded within the silicon containing matrix. The ceramic matrix composite component may further include a silicide layer sandwiched between the silicon containing matrix and the refractory fibers. A method of forming a ceramic matrix composite may include infiltrating a fluid that includes a refractory metal element containing compound into a fiber preform that includes fibers. The method may further include depositing the refractory metal element from the refractory metal element containing compound onto the fibers and forming, from the refractory metal element deposited onto the fibers, a refractory metal silicide.
Abstract translation: 本文描述了陶瓷基复合材料组件及其制造方法。 陶瓷基复合材料可以包括含硅基体和嵌入含硅基体内的难熔纤维。 陶瓷基复合材料组件还可以包括夹在含硅基质和耐火纤维之间的硅化物层。 形成陶瓷基质复合材料的方法可以包括将含有难熔金属元素的化合物的流体渗透到包括纤维的纤维预制棒中。 该方法还可以包括将难熔金属元素从含难熔金属元素的化合物沉积到纤维上，并从沉积在纤维上的耐火金属元素形成难熔金属硅化物。
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公开(公告)号：US20160368827A1
公开(公告)日：2016-12-22
申请号：US15188159
申请日：2016-06-21
Applicant: Rolls-Royce Corporation , Rolls-Royce North American Technologies, Inc. , Rolls-Royce High Temperature Composites, Inc.
Inventor： Sean E. Landwehr , Daniel K. Vetters , Ted J. Freeman , Robert J. Shinavski
IPC: C04B35/80 , C04B35/565 , C04B41/87
CPC classification number: C04B35/806 , B32B18/00 , C04B35/565 , C04B35/573 , C04B37/001 , C04B41/87 , C04B2235/3826 , C04B2235/422 , C04B2235/5244 , C04B2235/612 , C04B2235/614 , C04B2235/616 , C04B2235/77 , C04B2237/365 , C04B2237/38 , C04B2237/60 , C04B2237/61 , C04B2237/84 , F05D2240/11 , F05D2240/15 , F05D2300/20 , F05D2300/6033 , F23M2900/05004 , F23R3/002 , F23R3/007
Abstract: Integrated ceramic matrix composite components for use in gas turbine engines are disclosed along with methods for making the same. The methods include coinfiltrating a greenbody assembly with ceramic matrix to produce an integrated component.
Abstract translation: 公开了用于燃气涡轮发动机的集成陶瓷基复合材料组件及其制造方法。 所述方法包括将具有陶瓷基质的生物体组合体渗透以产生集成的组分。
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公开(公告)号：US20160279744A1
公开(公告)日：2016-09-29
申请号：US14974802
申请日：2015-12-18
Inventor： Stephen Isaiah Harris
CPC classification number: B23P6/04 , B23K9/00 , B23K9/0026 , B23K15/00 , B23K15/0006 , B23K26/0006 , B23K26/50 , B23K2103/08 , B23K2103/16 , B23K2103/52 , C04B35/565 , C04B35/62863 , C04B35/62868 , C04B35/62884 , C04B35/62894 , C04B35/806 , C04B2235/3826 , C04B2235/428 , C04B2235/5224 , C04B2235/5228 , C04B2235/5236 , C04B2235/524 , C04B2235/5244 , C04B2235/5248 , C04B2235/5472 , C04B2235/616 , H05B6/80
Abstract: A method for repairing a ceramic matrix composite (CMC) article including a ceramic material in a matrix including a metal alloy, wherein a localized region of the metal alloy has a defect. The method includes applying heat to the localized region for a time sufficient to increase the temperature of the metal alloy in the localized region above the melt temperature thereof and cause the metal alloy in the localized region to flow and seal the crack.
Abstract translation: 一种用于修复包括金属合金的基体中的陶瓷材料的陶瓷基复合材料（CMC）制品的方法，其中所述金属合金的局部区域具有缺陷。 该方法包括将热量施加到局部区域足够的时间以增加其熔融温度以上的局部区域中的金属合金的温度，并使局部区域中的金属合金流动并密封裂纹。
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公开(公告)号：US20160230570A1
公开(公告)日：2016-08-11
申请号：US15040527
申请日：2016-02-10
Inventor： Stephen L. Harris , Robert J. Shinavski , Richard W. Kidd , Sungbo Shim , Kang N. Lee
CPC classification number: F01D5/284 , C04B35/573 , C04B35/62863 , C04B35/62868 , C04B35/62894 , C04B35/806 , C04B41/009 , C04B41/5059 , C04B41/5096 , C04B41/52 , C04B41/89 , C04B2235/3826 , C04B2235/5276 , C04B2235/614 , C04B2235/616 , F01D5/282 , F01D5/288 , F01D11/122 , F05D2240/11 , F05D2300/222 , F05D2300/2261 , F05D2300/6032 , F05D2300/6033 , C04B35/565 , C04B35/584 , C04B35/58092 , C04B41/4529 , C04B41/4556 , C04B41/4527 , C04B41/5024 , C04B41/4582
Abstract: A ceramic matrix composite component for use in a gas turbine engine and method for making the same are described herein. The component comprising a body and an outer region. The body having a silicon containing ceramic composite. The outer region on an outer surface of the body.
Abstract translation: 这里描述了一种用于燃气涡轮发动机的陶瓷基复合材料组件及其制造方法。 所述部件包括主体和外部区域。 本体具有含硅陶瓷复合材料。 身体外表面上的外部区域。
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Patent Agency Ranking
公开(公告)号：US20160186611A1
公开(公告)日：2016-06-30
申请号：US14950776
申请日：2015-11-24
Applicant: Rolls-Royce North American Technologies, Inc. , Rolls-Royce High Temperature Composites Inc.
Inventor： Daniel K. Vetters , Joseph Doyle , Michael Jacquinto , Wesley Thibault
CPC classification number: F01D25/246 , F01D9/04 , F01D11/08 , F01D11/18 , F01D11/24 , F05D2220/32 , F05D2230/60 , F05D2230/64 , F05D2230/642 , F05D2240/11 , F05D2240/307 , F05D2250/38 , Y02T50/672
Abstract: A turbine shroud assembly or blade track assembly adapted to extend around a turbine wheel assembly is disclosed. The turbine shroud assembly includes a carrier and a blade track coupled to the carrier. The blade track is movable between a radially-inward position having a first inner diameter and a radially-outward position having a second inner diameter larger than the first inner diameter.
Abstract translation: 公开了一种适于围绕涡轮机叶轮组件延伸的涡轮机罩组件或叶片轨道组件。 涡轮机罩组件包括一个载体和一个连接到载体的叶片轨道。 刀片轨道可以在具有第一内径的径向向内位置和径向向外位置之间移动，其具有大于第一内径的第二内径。
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37.发明申请TURBINE BLISK INCLUDING CERAMIC MATRIX COMPOSITE BLADES AND METHODS OF MANUFACTURE 审中-公开包括陶瓷基复合材料的涡轮机和制造方法公开(公告)号：US20160130957A1
公开(公告)日：2016-05-12
申请号：US14937260
申请日：2015-11-10
Applicant: Rolls-Royce North American Technologies, Inc. , Rolls-Royce High Temperature Composites Inc.
Inventor： Ted J. Freeman , Todd Z. Engel
CPC classification number: F01D5/3061 , B23K1/0018 , B23K1/19 , B23K20/026 , B23K20/233 , B23K2101/001 , B23K2103/52 , F01D5/02 , F01D5/066 , F01D5/16 , F01D5/282 , F01D5/284 , F01D5/3023 , F01D5/303 , F01D5/3069 , F05D2220/32 , F05D2230/237 , F05D2230/60 , F05D2240/24 , F05D2300/10 , F05D2300/6033 , Y02T50/672
Abstract: In some embodiments, an apparatus includes a disk, a coupling member and a set of blades. The coupling member has a first surface and a second surface, and defines a set of openings between the first surface and the second surface. The first surface is configured to be coupled to the outer surface of the disk. A portion of each blade from the set of blades is disposed within an opening from the set of openings when the first surface of the coupling member is coupled to the outer surface of the disk such that the blade is coupled to the disk.
Abstract translation: 在一些实施例中，装置包括盘，联接构件和一组叶片。 联接构件具有第一表面和第二表面，并且在第一表面和第二表面之间限定一组开口。 第一表面被配置为联接到盘的外表面。 当联接构件的第一表面联接到盘的外表面上时，来自该组叶片的每个叶片的一部分设置在从一组开口的开口内，使得叶片联接到盘。
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公开(公告)号：US12188365B1
公开(公告)日：2025-01-07
申请号：US18528739
申请日：2023-12-04
Inventor： David J. Thomas , Christopher Downie , Aaron D. Sippel , Ted J. Freeman , Clark Snyder
Abstract: A turbine shroud assembly adapted for use with a gas turbine engine includes a shroud segment. The shroud segment includes a heat shield, an attachment flange, and a multi-layer coating. The heat shield extends circumferentially partway around the axis to define a portion of gas path for the gas turbine engine. The attachment feature extends radially outward from the heat shield. The multi-layer coating is applied to different surfaces of the heat shield and the attachment feature of the shroud segment.
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公开(公告)号：US20240408855A1
公开(公告)日：2024-12-12
申请号：US18807812
申请日：2024-08-16
Inventor： Sungbo Shim , Pathikumar Sellappan
Abstract: A method to form a machinable ceramic matrix composite comprises forming a porous ceramic multilayer on a surface of a fiber preform. In one example, the porous ceramic multilayer comprises a gradient in porosity in a direction normal to the surface. In another example, the porous ceramic multilayer includes low-wettability particles having a high contact angle with molten silicon, where an amount of the low-wettability particles in the porous ceramic multilayer varies in a direction normal to the surface. After forming the multilayer, the fiber preform is infiltrated with a melt, and the melt is cooled to form a ceramic matrix composite with a surface coating thereon. An outer portion of the surface coating is machined to form a ceramic matrix composite having a machined surface with a predetermined surface finish and/or dimensional tolerance.
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公开(公告)号：US12071380B2
公开(公告)日：2024-08-27
申请号：US17412686
申请日：2021-08-26
Applicant: Rolls-Royce High Temperature Composites Inc.
Inventor： Sungbo Shim , Pathikumar Sellappan
IPC: C04B35/80 , C04B35/626 , C04B35/628 , C04B35/657 , F01D5/28 , F01D25/00
CPC classification number: C04B35/80 , C04B35/62655 , C04B35/62863 , C04B35/62886 , C04B35/62894 , C04B35/657 , F01D5/284 , F01D25/005 , C04B2235/3418 , C04B2235/3826 , C04B2235/386 , C04B2235/3865 , C04B2235/5244 , C04B2235/5252 , C04B2235/612 , C04B2235/616 , C04B2235/9669
Abstract: A method to form a machinable ceramic matrix composite comprises forming a porous ceramic multilayer on a surface of a fiber preform. In one example, the porous ceramic multilayer comprises a gradient in porosity in a direction normal to the surface. In another example, the porous ceramic multilayer includes low-wettability particles having a high contact angle with molten silicon, where an amount of the low-wettability particles in the porous ceramic multilayer varies in a direction normal to the surface. After forming the porous ceramic multilayer, the fiber preform is infiltrated with a melt, and the melt is cooled to form a ceramic matrix composite with a surface coating thereon. An outer portion of the surface coating is more readily machinable than an inner portion of the surface coating. The outer portion of the surface coating is machined to form a ceramic matrix composite having a machined surface with a predetermined surface finish and/or dimensional tolerance.
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