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21. 发明公开

EP3450699A1 CERAMIC MATRIX COMPOSITE BLADE TRACK FOR A GAS TURBINE ENGINE AND METHOD OF MAKING THE SAME 有权
公开(公告)号：EP3450699A1
公开(公告)日：2019-03-06
申请号：EP18189087.2
申请日：2018-08-15
申请人： Rolls-Royce Corporation , Rolls-Royce North American Technologies, Inc.
发明人： Sippel, Aaron , Varney, Bruce , Freeman, Ted , Holley, Kevin
IPC分类号： F01D11/08 , C04B35/80
摘要： A gas turbine engine (10) may comprise a blade track (20, 220, 320) and a method of making the same. The blade track (20, 220, 320) may be constructed of ceramic matrix composite components including segments and joints.

22. 发明公开

EP3330498A1 TURBINE SHROUD WITH HANGER ATTACHMENT 有权
公开(公告)号：EP3330498A1
公开(公告)日：2018-06-06
申请号：EP17199820.6
申请日：2017-11-03
申请人： Rolls-Royce Corporation , Rolls-Royce North American Technologies, Inc.
发明人： Freeman, Ted , Sippel, Aaron , Vetters, Daniel , Thomas, David , Baucco, Alexandra
IPC分类号： F01D25/24
摘要： An assembly adapted for use in a gas turbine engine has a carrier component and a supported component. The assembly including a mounting system for coupling the supported component to the carrier component and a seal adapted to resist the movement of gasses between the supported component to the carrier component. In an illustrative embodiment, the assembly is a turbine shroud segment for blocking gasses from passing over turbine blades included in the gas turbine engine.

23. 发明公开

EP3088690A1 FULL HOOP BLADE TRACK WITH FLANGED SEGMENTS 有权转让
标题翻译： VOLLRING-SCHAUFELSPUR MIT GEFLANSCHTEN SEGMENTEN
公开(公告)号：EP3088690A1
公开(公告)日：2016-11-02
申请号：EP16165823.2
申请日：2016-04-18
申请人： Rolls-Royce Corporation , Rolls-Royce North American Technologies, Inc. , Rolls-Royce plc , Rolls-Royce High Temperature Composites, Inc.
发明人： Vetters, Daniel , Sippel, Aaron , Thomas, David , Eifert, Andrew , Davis, Paul , Jones, Simon , Hillier, Steven , Broadhead, Peter , Doyle, Joseph , Jacquinto, Michael , Thibault, Wesley , Shi, Jun , Townes, Roderick
IPC分类号： F01D25/24
摘要： A blade track assembly is disclosed. The blade track assembly comprises a plurality of ceramic matrix composite blade track segments (33, 34, 35) arranged circumferentially adjacent to one another around a central axis. Each of the blade track segments includes an arcuate runner (33R, 34R, 35R) extending in a circumferential direction around a portion of the central axis and is coupled to circumferentially adjacent blade track segments (33, 34, 35).
摘要翻译：公开了一种刀片轨道组件。刀片轨道组件包括围绕中心轴线彼此周向相邻布置的多个陶瓷基体复合刀片轨道段（33,34,35）。每个叶片轨道段包括在围绕中心轴线的一部分的圆周方向上延伸并连接到周向相邻的叶片轨道段（33,34,35）的弓形流道（33R，34R，35R）。

24. 发明公开

EP3088664A1 COMPOSITE KEYSTONED BLADE TRACK 有权转让
标题翻译：复合KEYSTONED刀片轨道
公开(公告)号：EP3088664A1
公开(公告)日：2016-11-02
申请号：EP16164265.7
申请日：2016-04-07
申请人： Rolls-Royce Corporation , Rolls-Royce North American Technologies, Inc. , Rolls-Royce plc
发明人： Vetters, Daniel , Sippel, Aaron , Thomas, David , Eifert, Andrew , Davis, Paul , Jones, Simon , Hillier, Steven , Broadhead, Peter , Varney, Bruce , Walston, Jeffrey
IPC分类号： F01D5/14 , F01D5/24 , F01D9/04 , F01D25/24
CPC分类号： F01D11/122 , C04B35/803 , C04B35/806 , C04B35/83 , C04B2235/5252 , C04B2235/94 , F01D11/12 , F01D25/005 , F01D25/12 , F04D29/164 , F04D29/526 , F05D2220/32 , F05D2230/60 , F05D2240/11 , F05D2240/55 , F05D2260/22141 , F05D2260/52 , F05D2300/6033 , Y02T50/672
摘要： A blade track for a gas turbine engine, the blade track (20) comprises a plurality of blade track segments (22) each comprised of ceramic-matrix composite materials and shaped to extend part-way around a central axis (A). Each blade track segment (22) includes opposing circumferential end faces (21, 23) and a radially outer surface (25) extending between the end faces. A composite-lock structure (24) is positioned to engage the outer surfaces (25) of the blade track segments (22). The composite-lock structure (24) includes at least one reinforcement fiber (52) of ceramic-containing material suspended in ceramic-matrix material. The blade track segments (22) are positioned circumferentially around the central axis (A) to form a ring. The end faces (21, 23) of the blade track segments (22) are engaged with one another, and the composite-lock structure (24) is configured to provide a radially-inward force toward the central axis against the blade track segments (22) such that each blade track segment (22) acts as a keystone to maintain the form of the ring.
摘要翻译：一种用于燃气涡轮发动机的叶片轨道，所述叶片轨道（20）包括多个叶片轨道段（22），每个叶片轨道段由陶瓷 - 基质复合材料组成并且成形为围绕中心轴线（A）部分地延伸。每个叶片轨道段（22）包括相对的周向端面（21,23）和在端面之间延伸的径向外表面（25）。复合锁定结构（24）定位成接合叶片轨道段（22）的外表面（25）。复合锁定结构（24）包括至少一个悬挂在陶瓷基质材料中的含陶瓷材料的增强纤维（52）。叶片轨道段（22）围绕中心轴线（A）周向定位以形成环。叶片轨道段（22）的端面（21,23）彼此接合，并且复合锁定结构（24）构造成提供朝向中心轴线抵靠叶片轨道段的径向向内的力使得每个叶片轨道段（22）充当保持环的形式的梯形。

25. 发明授权

EP3181814B1 FIBER REINFORCED AIRFOIL 有权
公开(公告)号：EP3181814B1
公开(公告)日：2020-09-02
申请号：EP16204722.9
申请日：2016-12-16
申请人： Rolls-Royce Corporation
发明人： Freeman, Ted , Engel, Todd , Chamberlain, Adam , Sippel, Aaron , Landwehr, Sean
IPC分类号： F01D5/14 , F01D5/28 , F04D29/02 , F04D29/32 , F04D29/54

26. 发明公开

EP3181814A1 FIBER REINFORCED AIRFOIL 有权
标题翻译：纤维增强翼型
公开(公告)号：EP3181814A1
公开(公告)日：2017-06-21
申请号：EP16204722.9
申请日：2016-12-16
申请人： Rolls-Royce Corporation
发明人： Freeman, Ted , Engel, Todd , Chamberlain, Adam , Sippel, Aaron , Landwehr, Sean
IPC分类号： F01D5/14 , F01D5/28 , F04D29/02 , F04D29/32 , F04D29/54
摘要： A CMC airfoil (10) and a method of manufacturing (60-64) a CMC airfoil (10) is provided, where the airfoil (10) comprises a core (12) and a shell (14). The core (12) comprises core ceramic fibers (16) extending along a span (80) of the airfoil (10). The shell (14) surrounds the core (12) and includes shell ceramic fibers (38,40). Substantially all of the core ceramic fibers (16) are arranged in a radial direction (80). The shell ceramic fibers (38,40) may be woven or braided. The braided fibers may be arranged in a braid angle (78), preferably being between 25° and 75° with respect to the radial axis (80). The core ceramic fibers (16) are preferably made of a ceramic material having a higher creep resistance than the material forming the shell ceramic fibers (38,40). Thus, the CMC airfoil (10) is able to tolerate high stress mechanical conditions.
摘要翻译：提供CMC翼型件（10）和制造（60-64）CMC翼型件（10）的方法，其中翼型件（10）包括芯部（12）和壳体（14）。芯部（12）包括沿着翼型件（10）的跨度（80）延伸的芯部陶瓷纤维（16）。壳体（14）围绕芯体（12）并且包括壳体陶瓷纤维（38,40）。基本上所有的芯陶瓷纤维（16）沿径向（80）排列。壳陶瓷纤维（38,40）可以被编织或编织。编织纤维可以布置成编织角度（78），优选相对于径向轴线（80）在25°和75°之间。芯陶瓷纤维（16）优选由具有比形成壳陶瓷纤维（38,40）的材料更高的抗蠕变性的陶瓷材料制成。因此，CMC翼型件（10）能够承受高应力机械条件。

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