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公开(公告)号：US20210355962A1
公开(公告)日：2021-11-18
申请号：US17272735
申请日：2019-08-28
Applicant: SAFRAN AIRCRAFT ENGINES
Inventor： Florent Louis Andre ROGNIN , Clement BOUROLLEAU , Serge DOMINGUES , Vincent Pascal FIORE , Anwer SIRAJ
Abstract: The invention relates to a fan casing (200) for an aircraft turbomachine, such as a jet engine, said casing having a one-piece annular body (202), said body having a radially internal annular surface (206), a first annular portion (208) of which is made of abradable material, characterized in that a second annular portion (210) of said internal surface comprises blind holes (212) that confer acoustic properties on said second portion.
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公开(公告)号：US20220170431A1
公开(公告)日：2022-06-02
申请号：US17428247
申请日：2020-02-07
Applicant: SAFRAN AIRCRAFT ENGINES
Inventor： Anwer SIRAJ , CLÉMENT BOUROLLEAU , SERGE DOMINGUES , VINCENT PASCAL FIORE , FLORENT LOUIS ANDRÉ ROGNIN
Abstract: A ring assembly has a housing made of woven composite material carrying on its radially inner face an acoustic panel with a cellular structure covered with a composite material. The housing includes at least one radial recess in which is engaged at least one radially outwardly projecting part of the radially outer face of the acoustic panel.
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Patent Agency Ranking
公开(公告)号：US20220120196A1
公开(公告)日：2022-04-21
申请号：US17426901
申请日：2020-01-17
Applicant: SAFRAN AIRCRAFT ENGINES
Inventor： Clément BOUROLLEAU , Alexandre BRANCO , Serge DOMINGUES , Vincent Pascal FIORE , Anwer SIRAJ
Abstract: A gas turbine fan casing made of composite material with a fibrous reinforcement includes a plurality of superimposed turns of a strip-shaped fibrous texture having a three-dimensional weaving between a plurality of layers of warp yarns and a plurality of layers of weft yarns, the fibrous reinforcement being densified by a matrix. The fibrous texture includes at least one lateral section of variable thickness in which the weft yarns have a size or a count different from the size or the count of the weft yarns of the plurality of layers of weft yarns present in the remainder of the fibrous texture.
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公开(公告)号：US20240295177A1
公开(公告)日：2024-09-05
申请号：US18003403
申请日：2021-06-29
Applicant: SAFRAN AIRCRAFT ENGINES
Inventor： Clement BOUROLLEAU , Clementine ARNOLD , Alexandre BRANCO , Serge DOMINGUES , Thomas DUPAYS , Vincent Pascal FIORE , Baptiste LEBLON , Anwer SIRAJ
CPC classification number: F01D11/125 , F01D21/045 , F05D2220/36 , F05D2300/2102 , F05D2300/224
Abstract: A housing for an aircraft turbomachine, including an annular casing extending around an axis A and having an internal annular surface, the housing also including an annular abradable support cartridge that is fixed against the internal annular surface, the abradable support cartridge has a reinforced coating including a fibrous texture reinforcement embedded in a resin matrix, the fibrous texture reinforcement including a stack of fibrous texture plies, wherein the stack of plies includes at least one ply made of Kevlar® or of glass fibres.
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公开(公告)号：US20220333496A1
公开(公告)日：2022-10-20
申请号：US17753547
申请日：2020-09-09
Applicant: SAFRAN AIRCRAFT ENGINES
Inventor： Thomas DUPAYS , Clement BOUROLLEAU , Coline POULENC , Anwer SIRAJ
Abstract: The invention relates to a method for manufacturing an aircraft turbine engine housing, the housing (23) comprising: an annular shell (29) with axis A; —an annular element (24; 253, 254) attached to the inside of the shell (29), the annular element comprising a body (25) made of NIDA-type cellular material and comprising a downstream portion (252) covered with an abradable material (26), and an upstream portion (251) without abradable material, the body (25) extending in a continuous manner from the upstream portion (251) to the downstream portion (252), the method comprising: —manufacturing the annular element in the form of a continuous annular body, —cutting the annular body into segments (253, 254), —attaching the segments to the shell, and —depositing the abradable material (26) onto the inside surface (25a) of the downstream portion (252).
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公开(公告)号：US20220099108A1
公开(公告)日：2022-03-31
申请号：US17425455
申请日：2020-01-30
Applicant: SAFRAN AIRCRAFT ENGINES
Inventor： Clément BOUROLLEAU , Vincent Pascal FIORE , Anwer SIRAJ , Alexandre BRANCO , Serge DOMINGUES
Abstract: A fan casing for an aircraft turbomachine includes an annular body extending around an axis and equipped with an annular attachment flange at each of its axial ends. The casing further includes an annular coating made from abradable material, wherein the body is made from a composite material, and further includes an annular stiffener that is arranged inside the body and that carries the coating. The stiffener includes an annular ring, a radially outer face of which is separated radially from the body and a radially inner face of which receives the coating. The stiffener further includes annular attachment tabs configured to the wall to the body.
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公开(公告)号：US20210340881A1
公开(公告)日：2021-11-04
申请号：US17273528
申请日：2019-09-03
Applicant: SAFRAN AIRCRAFT ENGINES
Inventor： Clément BOUROLLEAU , Serge DOMINGUES , Vincent Pascal FIORE , Florent Louis André ROGNIN , Anwer SIRAJ
Abstract: 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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