Patents by Inventor Vincent Pascal FIORE
Vincent Pascal FIORE has filed for patents to protect the following inventions. This listing includes patent applications that are pending as well as patents that have already been granted by the United States Patent and Trademark Office (USPTO).
-
Patent number: 11988107Abstract: A housing for an aircraft turbine engine includes an annular body extending around an axis A. The body includes a securing flange extending radially outwards at each of the axial ends thereof, and an abradable layer arranged inside the body. A method for manufacturing the housing includes a step b) of bonding the layer to the first surface, during which the housing is heated and compressed by a system present at least partially inside the housing. The method further includes, prior to step b), a step a) of mounting at least two tools between the flanges, each of the tools being located in a circumferential area outside the body so as to exert bearing forces in opposite axial directions on the flanges.Type: GrantFiled: June 26, 2020Date of Patent: May 21, 2024Assignee: SAFRAN AIRCRAFT ENGINESInventors: Vincent Pascal Fiore, Clémentine Arnold, Clément Bourolleau, Thomas Dupays, Serge Domingues
-
Patent number: 11891910Abstract: 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.Type: GrantFiled: September 3, 2019Date of Patent: February 6, 2024Assignee: SAFRAN AIRCRAFT ENGINESInventors: Clément Bourolleau, Serge Domingues, Vincent Pascal Fiore, Florent Louis André Rognin, Anwer Siraj
-
Patent number: 11879412Abstract: 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.Type: GrantFiled: February 7, 2020Date of Patent: January 23, 2024Assignee: SAFRAN AIRCRAFT ENGINESInventors: Anwer Siraj, Clément Bourolleau, Serge Domingues, Vincent Pascal Fiore, Florent Louis André Rognin
-
Patent number: 11788558Abstract: A fan casing for an aircraft turbomachine, the casing including a one-piece annular body, the one piece annular body including a radially internal annular surface, a first annular portion of which is made of an abradable material, wherein a second annular portion of the internal surface comprises blind holes conferring acoustic properties to the second portion.Type: GrantFiled: August 28, 2019Date of Patent: October 17, 2023Assignee: SAFRAN AIRCRAFT ENGINESInventors: Florent Louis Andre Rognin, Clement Bourolleau, Serge Domingues, Vincent Pascal Fiore, Anwer Siraj
-
Patent number: 11788434Abstract: 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.Type: GrantFiled: July 10, 2020Date of Patent: October 17, 2023Assignees: SAFRAN AIRCRAFT ENGINES, SAFRAN AEROSPACE COMPOSITESInventors: Vincent Pascal Fiore, Gatien Frisoni, Foster Alexander Maxwell, Steven Meserve, Jeffrey Steven Sherman
-
Patent number: 11702961Abstract: 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.Type: GrantFiled: January 17, 2020Date of Patent: July 18, 2023Assignee: SAFRAN AIRCRAFT ENGINESInventors: Clément Bourolleau, Alexandre Branco, Serge Domingues, Vincent Pascal Fiore, Anwer Siraj
-
Publication number: 20220268175Abstract: A housing for an aircraft turbine engine includes an annular body extending around an axis A. The body includes a securing flange extending radially outwards at each of the axial ends thereof, and an abradable layer arranged inside the body. A method for manufacturing the housing includes a step b) of bonding the layer to the first surface, during which the housing is heated and compressed by a system present at least partially inside the housing. The method further includes, prior to step b), a step a) of mounting at least two tools between the flanges, each of the tools being located in a circumferential area outside the body so as to exert bearing forces in opposite axial directions on the flanges.Type: ApplicationFiled: June 26, 2020Publication date: August 25, 2022Applicant: SAFRAN AIRCRAFT ENGINESInventors: Vincent Pascal Fiore, Clémentine Arnold, Clément Bourolleau, Thomas Dupays, Serge Domingues
-
Publication number: 20220243617Abstract: 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.Type: ApplicationFiled: July 10, 2020Publication date: August 4, 2022Inventors: Vincent Pascal FIORE, Gatien FRISONI, Foster Alexander MAXWELL, Steven MESERVE, Jeffrey Steven SHERMAN
-
Publication number: 20220170431Abstract: 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.Type: ApplicationFiled: February 7, 2020Publication date: June 2, 2022Applicant: SAFRAN AIRCRAFT ENGINESInventors: Anwer SIRAJ, CLÉMENT BOUROLLEAU, SERGE DOMINGUES, VINCENT PASCAL FIORE, FLORENT LOUIS ANDRÉ ROGNIN
-
Publication number: 20220120196Abstract: 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.Type: ApplicationFiled: January 17, 2020Publication date: April 21, 2022Inventors: Clément BOUROLLEAU, Alexandre BRANCO, Serge DOMINGUES, Vincent Pascal FIORE, Anwer SIRAJ
-
Publication number: 20220099108Abstract: 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.Type: ApplicationFiled: January 30, 2020Publication date: March 31, 2022Applicant: SAFRAN AIRCRAFT ENGINESInventors: Clément BOUROLLEAU, Vincent Pascal FIORE, Anwer SIRAJ, Alexandre BRANCO, Serge DOMINGUES
-
Publication number: 20210355962Abstract: 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.Type: ApplicationFiled: August 28, 2019Publication date: November 18, 2021Inventors: Florent Louis Andre ROGNIN, Clement BOUROLLEAU, Serge DOMINGUES, Vincent Pascal FIORE, Anwer SIRAJ
-
Publication number: 20210340881Abstract: 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.Type: ApplicationFiled: September 3, 2019Publication date: November 4, 2021Inventors: Clément BOUROLLEAU, Serge DOMINGUES, Vincent Pascal FIORE, Florent Louis André ROGNIN, Anwer SIRAJ