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公开(公告)号：US20240209742A1
公开(公告)日：2024-06-27
申请号：US18088990
申请日：2022-12-27
CPC分类号： F01D5/282 , F01D5/147 , F01D5/30 , F05D2300/6034
摘要： A composite blade assembly for a turbine engine, the composite blade assembly having a core and a laminate skin. The core having a composite structure. The laminate skin having at least one composite ply. The laminate skin having a first portion forming a first angle relative to a horizontal plane, and a second portion forming a second angle relative to the horizontal plane.
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公开(公告)号：US11920477B2
公开(公告)日：2024-03-05
申请号：US18074726
申请日：2022-12-05
申请人： RTX CORPORATION
发明人： Olivier H. Sudre
CPC分类号： F01D11/003 , F16J15/26 , F05D2240/55 , F05D2300/6033 , F05D2300/6034
摘要： A seal includes a ceramic matrix composite ply having woven ceramic-based fibers in a ceramic-based matrix. The ceramic matrix composite ply has at least one bend formed about a bend axis and defines at least one rounded portion. A sealed assembly and a method of making a seal are also disclosed.
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公开(公告)号：US20240044254A1
公开(公告)日：2024-02-08
申请号：US17881771
申请日：2022-08-05
发明人： David Raju Yamarthi , Vasanth Kumar Balaramudu , Vishnu Vardhan Venkata Tatiparthi , Paul Mathew , Douglas Lorrimer Armstrong , Gary Willard Bryant, JR. , Nuthi Srinivas
CPC分类号： F01D5/147 , F01D5/282 , F05D2250/25 , F05D2240/30 , F05D2300/612 , F05D2300/6034
摘要： An airfoil assembly and a method of manufacturing the same are provided, the airfoil assembly defining a span axis, a root end, and a tip end. The airfoil assembly includes a reinforcement structure comprising a first helical support structure wrapped around the span axis between the root end and the tip end and a second helical support structure wrapped around the span axis between the root end and the tip end; a polymeric matrix material positioned at least partially around the reinforcement structure; and an outer skin positioned around the reinforcement structure and the polymeric matrix material.
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公开(公告)号：US11891910B2
公开(公告)日：2024-02-06
申请号：US17273528
申请日：2019-09-03
发明人： Clément Bourolleau , Serge Domingues , Vincent Pascal Fiore , Florent Louis André Rognin , Anwer Siraj
IPC分类号： F01D25/24 , B29C70/22 , B29C70/32 , B29C70/86 , B29L31/00 , F01D25/28 , F01D25/26 , F01D5/14 , F01D5/28
CPC分类号： F01D25/24 , B29C70/222 , B29C70/32 , B29C70/865 , B29L2031/7504 , F01D5/14 , F01D5/141 , F01D5/282 , F01D25/26 , F01D25/28 , F05D2230/21 , F05D2240/14 , F05D2250/75 , F05D2300/6012 , F05D2300/6031 , F05D2300/6034
摘要： A method for manufacturing a composite-material casing for a gas turbine, includes producing by three-dimensional weaving a fiber texture in the form of a strip, winding of the fiber texture around several superimposed turns on a mandrel with a profile corresponding to that of the casing to be manufactured in order to obtain a fiber preform of a shape corresponding to that of the casing to be manufactured, and densifying the fiber preform by a matrix. During the winding of the last turn of the fiber texture on the mandrel, at least one stiffening element is interposed between the before-last turn and the last turn of the fiber texture. The stiffening element projects over the outer surface of the before-last turn of the fiber texture. The stiffening element has an axial section of omega-type shape.
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公开(公告)号：US11840964B2
公开(公告)日：2023-12-12
申请号：US17881225
申请日：2022-08-04
申请人： ROLLS-ROYCE plc
发明人： Fiona Halliday , Mark Spruce
CPC分类号： F02C7/36 , B29C70/28 , F01D5/06 , F16C3/026 , B29L2031/75 , F05D2240/60 , F05D2300/6034 , F05D2300/614 , F16C2208/02 , F16C2240/30 , F16C2360/23
摘要： A shaft component, which in particular can be connected or is connected to the input or output side of a gear box in a gas turbine engine, in particular an aircraft engine, wherein the shaft component has at least two regions comprising fiber reinforced plastic, with fibers in the at least two regions differing in their composition, their geometric properties, their density, their radial position, their axial position and/or in their fiber orientation in the shaft component.
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公开(公告)号：US11828184B2
公开(公告)日：2023-11-28
申请号：US17908065
申请日：2021-02-19
CPC分类号： F01D11/008 , B29C70/24 , B29C70/72 , F01D5/147 , F01D5/282 , F05D2220/36 , F05D2240/80 , F05D2250/712 , F05D2300/44 , F05D2300/6034
摘要： A composite platform for an aircraft turbine engine fan includes a wall of elongate shape that is configured to extend between two fan blades. The wall has an aerodynamic external face and an internal face on which is disposed a fixing tab configured to be fixed to a fan disc. A method for manufacturing the composite platform includes the steps of: a) producing a preform by three-dimensionally weaving of fibers, b) unbinding some of the fibers of the preform to detach at least one longitudinal layer of fibers from the rest of the preform, c) inserting a metal reinforcement between this layer and the rest of the preform, and d) injecting a resin into the preform so as to form said wall and secure the reinforcement to this wall.
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公开(公告)号：US11795836B2
公开(公告)日：2023-10-24
申请号：US17996024
申请日：2021-04-12
申请人： SAFRAN
IPC分类号： F01D25/00 , B29C45/14 , B29C45/16 , F01D9/04 , B29K307/04 , B29K705/08 , B29L31/08 , B29C64/147 , B29C70/02 , B29C70/08 , B29C64/205 , B29C70/20 , B29C70/88
CPC分类号： F01D25/005 , B29C45/14336 , B29C45/14631 , B29C45/1671 , F01D9/041 , B29C64/147 , B29C64/205 , B29C70/021 , B29C70/08 , B29C70/085 , B29C70/202 , B29C70/885 , B29K2307/04 , B29K2705/08 , B29L2031/082 , F05D2220/323 , F05D2230/21 , F05D2240/12 , F05D2240/123 , F05D2300/6032 , F05D2300/6034 , F05D2300/615
摘要： A method for manufacturing a blade made of composite material for a turbine engine, in particular of an aircraft, the steps of injecting a resin in order to impregnate a fibrous preform woven in three dimensions and polymerizing the resin so as to form the blade that includes an airfoil, one longitudinal end of which is connected to a platform. The platform includes pressure and suction portions connected to the airfoil by a fillet, wherein a separation is formed in the fibrous preform between the pressure and suction portions. The method further includes reinforcing a leading edge of the airfoil; and reinforcing the fillets by integration of a metal reinforcement on at least one part of the pressure and suction portions of the platform and in the separation.
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公开(公告)号：US11668264B2
公开(公告)日：2023-06-06
申请号：US16920185
申请日：2020-07-02
CPC分类号： F02K1/56 , B29C70/06 , B64D33/04 , F02K1/72 , B29L2031/08 , F05D2220/323 , F05D2230/20 , F05D2230/31 , F05D2240/129 , F05D2300/603 , F05D2300/6034
摘要： Thrust reverser composite cascade (1), comprising at least one longitudinal wall (15) and transverse walls (14) connecting to this longitudinal wall, characterized in that the longitudinal wall comprises at least one continuous longitudinal fibre bundle (19) and the transverse walls each comprise at least one continuous transverse fibre bundle (23) crossing the longitudinal bundle, so that the intersections (16) of the transverse and longitudinal walls are structurally bridged in both directions by the reinforcing continuous longitudinal and transverse fibre bundles.
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公开(公告)号：US20190211705A1
公开(公告)日：2019-07-11
申请号：US15868289
申请日：2018-01-11
发明人： Colin J. Kling
CPC分类号： F01D21/045 , B29C70/228 , B29C70/24 , B29C70/70 , B29C70/72 , B29D99/0014 , B32B1/08 , B32B3/08 , B32B3/28 , B32B5/26 , B32B2260/021 , D04C1/06 , D10B2401/063 , D10B2505/02 , F01D25/24 , F05D2220/32 , F05D2220/36 , F05D2300/603 , F05D2300/6034
摘要： A gas turbine engine component includes a tubular body section including a plurality of fiber wraps encompassed within a matrix composition and one or more integrally-formed stiffeners extending from an outer surface of the body section and in a component circumferential direction around the body section. The stiffener includes one or more fiber wraps extending radially outwardly from the body section over a form and to the body section from the form.
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公开(公告)号：US10018055B2
公开(公告)日：2018-07-10
申请号：US14951651
申请日：2015-11-25
发明人： Thomas J. Robertson
CPC分类号： F01D5/282 , F01D5/02 , F01D5/147 , F01D11/008 , F05D2220/32 , F05D2220/36 , F05D2240/30 , F05D2240/80 , F05D2300/6034 , F05D2300/614 , Y02T50/672
摘要： A fan platform section may include a flow path portion with a plurality of composite plies. A first composite ply in the plurality of composite plies may include directional fibers. The directional fibers may be configured to prevent twisting of the flow path section in response to a centripetal load. The fan platform section may include a second composite ply in the plurality of composite plies. The second composite ply may include directional fibers. The directional fibers in the first composite ply may be orthogonal with respect to the directional fibers in the second composite ply.
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