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

IPC: F04D29/52 ,  F02C6/20 ,  F04D19/00

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.

公开(公告)号：US20220243617A1

公开(公告)日：2022-08-04

申请号：US17626322

申请日：2020-07-10

Applicant: SAFRAN AIRCRAFT ENGINES ,  SAFRAN AEROSPACE COMPOSITES

Inventor： Vincent Pascal FIORE ,  Gatien FRISONI ,  Foster Alexander MAXWELL ,  Steven MESERVE ,  Jeffrey Steven SHERMAN

IPC: F01D25/24 ,  B29C65/00

Abstract: Method for manufacturing a casing of an aircraft turbomachine, the casing including an annular shell extending about an axis A and made of a composite material including fibres that are woven and immersed in a resin, the annular layer including an abradable material arranged inside the shell, and covering a first inner annular surface of an intermediate section of the shell, the method including a step of gluing the layer on the first surface, during which the casing is heated and compressed by a system that is present at least partially inside the casing, wherein, prior to the heating and compression of the casing, a forming tool is mounted inside the casing and is made of two rings.

公开(公告)号：US20250122813A1

公开(公告)日：2025-04-17

申请号：US18692544

申请日：2022-09-14

Applicant: SAFRAN AIRCRAFT ENGINES

Inventor： Vincent Pascal FIORE ,  Clément BOUROLLEAU ,  Alexandre BRANCO ,  Serge Emmanuel DOMINGUES

IPC: F01D25/24

Abstract: A method for producing casing for an aircraft turbine engine includes a first step of manufacturing an annular shell having an axis A made of a composite material in a mold that includes an annular cavity that receives the preform. A resin is injected into the cavity and subsequently polymerized. During a second step, at least one axial abutment means is arranged inside the shell, and during a third step, the annular cartridge made of an abradable material is arranged inside the annular shell in contact with the axial abutment means. A fourth step includes bonding the annular cartridge to the first inner annular surface. The first and second steps are simultaneous, and the at least one axial abutment means is molded with the preform in the mold.

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

IPC: F01D25/24 ,  F01D21/04 ,  B29C70/24 ,  B29C70/32

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.

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

IPC: F01D11/12 ,  F01D21/04

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.

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

IPC: F04D29/52 ,  F02C3/06

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.

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

IPC: F01D25/24 ,  B29C70/22 ,  B29C70/86 ,  B29C70/32

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.