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公开(公告)号：US20240229669A1
公开(公告)日：2024-07-11
申请号：US18561861
申请日：2022-05-13
IPC分类号： F01D11/00
CPC分类号： F01D11/008 , F05D2220/36 , F05D2300/603
摘要： The present invention relates to a platform for a fan assembly, comprising a flow passage wall extending in an axial direction having an upstream end and a downstream end, and comprising two axial stiffeners. The platform comprises radial retention means positioned at the upstream end and at the downstream end of the flow passage wall, the radial retention means being designed to each define a sliding connection with a corresponding shroud of the fan assembly and in that it comprises tangential retention means designed to define a sliding pivot connection between the platform and a disc of the fan assembly.
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公开(公告)号：US20230193766A1
公开(公告)日：2023-06-22
申请号：US18010751
申请日：2021-06-09
CPC分类号： F01D5/282 , F01D5/147 , B29C70/86 , B29C70/222 , B29C70/34 , F05D2220/32 , F05D2230/23 , F05D2240/30 , B29L2031/082
摘要： A blade for an aircraft gas turbine engine includes, in a longitudinal direction, a blade root, a shank and an aerofoil body, the aerofoil body extending in the longitudinal direction between the shank and a blade tip and in a transverse direction between a leading edge made of metal material and a trailing edge. The blade includes a blade core made of composite material having a three-dimensional woven fibrous reinforcement forming the blade root, the shank and a part of the aerofoil body. The blade also includes a skin made of composite material having a two-dimensional woven fibrous reinforcement surrounding the aerofoil body part of the blade core, the skin being interposed between the leading edge made of metal material and a front edge of the aerofoil body part of the blade core to define a thinned leading edge portion, the skin including one or more two-dimensional woven plies.
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3.发明申请公开(公告)号：US20230027670A1
公开(公告)日：2023-01-26
申请号：US17910514
申请日：2021-03-11
摘要： The present invention relates to a blade comprising: - a structure made of composite material; - a blade root attachment part comprising a wall delimiting a cavity, a first opening formed in the wall and a second opening located under the blade root portion, the structure made of composite material extending through the first opening; - two locking parts configured to axially abut against a shoulder of the attachment part and to bear against the blade root portion; and - a cover for compressing the blade root portion against the locking parts.
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公开(公告)号：US20230010778A1
公开(公告)日：2023-01-12
申请号：US17757348
申请日：2020-12-17
摘要： Fan or propeller vane (1) for an aircraft turbomachine, the vane being made from a composite material and comprising a blade (2) and a base (3), the base being formed by a longitudinal end (41) of a spar (4) which is formed by a fibrous reinforcement formed from threads woven in three dimensions and a portion (42) of which extends inside the blade (2), the blade (2) having an aerodynamic profile which is defined by a skin (5) which is formed by woven threads and which surrounds the portion of the spar, the spar (4) and the skin (5) being embedded in a polymerised resin, characterised in that the portion (42) of the spar comprises projecting longitudinal stiffening members (6) which together delimit spaces (8) for receiving longitudinal inserts (7) which are formed from a honeycomb material.
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