Patents by Inventor Benoit Carrere
Benoit Carrere 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).
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Publication number: 20230407816Abstract: A turbomachine turbine assembly having a longitudinal axis and including an exhaust casing, an ejection cone arranged downstream of the exhaust casing, the ejection cone having an outer annular wall for the flow of a primary air stream and an acoustic box arranged radially inside said outer annular wall. The acoustic box can include a radially inner annular wall and a connection member interposed longitudinally between the exhaust casing and the inner annular wall of the ejection cone. The connection member can be fastened to the exhaust casing and to the inner annular wall. The upstream end of the outer annular wall can be connected to the connection member with a degree of freedom in the radial direction and a degree of freedom in the longitudinal direction.Type: ApplicationFiled: October 29, 2021Publication date: December 21, 2023Inventors: Eric CONETE, Benoit CARRERE, Thomas VANDELLOS
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Publication number: 20230407814Abstract: An assembly for a turbomachine with a longitudinal axis having an exhaust cone with an outer annular wall for the flow of a primary airflow and an annular box arranged radially inside the outer annular wall, an exhaust casing arranged upstream of and connected to the exhaust cone. One end of the outer annular wall or one end of the annular box may be free to move relative to and have no mechanical connection with the exhaust cone or the exhaust casing.Type: ApplicationFiled: November 4, 2021Publication date: December 21, 2023Inventors: Thomas VANDELLOS, Benoit CARRERE, Eric CONETE, Jean-Philippe JORET, Vincent DEVANLAY, Clément Marie Benoît ROUSSILLE
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Patent number: 11821387Abstract: The invention relates to an assembly for an aircraft turbomachine, comprising a central element (1) for the ejection of gas, and a connecting flange (9) interposed between, upstream, a gas outlet (22a) made of metal for a turbomachine, and, at the downstream end, the central element (1). The connecting flange comprises an annular portion (9a) and flexible tabs (11) having axially: a first end (111a) where the tab is connected to the said annular portion, and a second free end (111b), projecting radially inwardly with respect to the first end and to which said tab is attached with the central element (1).Type: GrantFiled: September 2, 2020Date of Patent: November 21, 2023Assignee: SAFRAN CERAMICSInventors: Eric Conete, Benoit Carrere
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Patent number: 11519361Abstract: An assembly for an aircraft turbojet engine is described. The assembly includes a central gas-exhaust element and a connecting flange interposed between, upstream, a metallic outlet of a turbojet engine and, downstream, the central element. The connecting flange consists of an annular part and flexible lugs having axially: a first end where the lug is connected to the annular part, and a second free end, projecting radially outwards from the first end and towards which the lug is fixed with the central element.Type: GrantFiled: August 9, 2019Date of Patent: December 6, 2022Assignee: SAFRAN CERAMICSInventors: Eric Conete, Benoit Carrere
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Patent number: 11512666Abstract: A structure for the nacelle of an aircraft propulsion unit includes a first skin and stiffeners arranged to hold acoustic treatment modules against the first skin. Each acoustic treatment module includes a honeycomb core and a second skin, such that the honeycomb core is sandwiched between the first skin and the second skin. Such a structure allows the structural reinforcement function provided by the stiffeners to be separated from the acoustic treatment function performed by the acoustic treatment modules which are simply bearing on the first skin.Type: GrantFiled: July 6, 2020Date of Patent: November 29, 2022Assignees: Safan Nacelles, Safran CeramicsInventors: Florent Bouillon, Franck Dupe, Benoît Carrere, Bertrand Desjoyeaux
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Publication number: 20220341373Abstract: The invention relates to an assembly for an aircraft turbomachine, comprising a central element (1) for the ejection of gas, and a connecting flange (9) interposed between, upstream, a gas outlet (22a) made of metal for a turbomachine, and, at the downstream end, the central element (1). The connecting flange comprises an annular portion (9a) and flexible tabs (11) having axially: a first end (111a) where the tab is connected to the said annular portion, and a second free end (111b), projecting radially inwardly with respect to the first end and to which said tab is attached with the central element (1).Type: ApplicationFiled: September 2, 2020Publication date: October 27, 2022Inventors: Eric CONETE, Benoit CARRERE
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Publication number: 20210293201Abstract: An assembly for an aircraft turbojet engine is described. The assembly includes a central gas-exhaust element and a connecting flange interposed between, upstream, a metallic outlet of a turbojet engine and, downstream, the central element. The connecting flange consists of an annular part and flexible lugs having axially: a first end where the lug is connected to the annular part, and a second free end, projecting radially outwards from the first end and towards which the lug is fixed with the central element.Type: ApplicationFiled: August 9, 2019Publication date: September 23, 2021Applicant: SAFRAN CERAMICSInventors: Eric Conete, Benoit Carrere
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Publication number: 20200339243Abstract: A structure for the nacelle of an aircraft propulsion unit includes a first skin and stiffeners arranged to hold acoustic treatment modules against the first skin. Each acoustic treatment module includes a honeycomb core and a second skin, such that the honeycomb core is sandwiched between the first skin and the second skin. Such a structure allows the structural reinforcement function provided by the stiffeners to be separated from the acoustic treatment function performed by the acoustic treatment modules which are simply bearing on the first skin.Type: ApplicationFiled: July 6, 2020Publication date: October 29, 2020Applicants: Safran Nacelles, Safran CeramicsInventors: Florent BOUILLON, Franck DUPE, Benoît CARRERE, Bertrand DESJOYEAUX
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Patent number: 10066581Abstract: The invention relates to an aeroengine after-body assembly comprising an exhaust casing made of metal having a plurality of arms extending radially between an inner shroud and an outer shroud. The assembly comprises at least one axisymmetric part made of composite material extending between an upstream end fastened to said exhaust casing and a downstream end that is free. In accordance with the invention, the axisymmetric part has an annular portion at its upstream end, which annular portion includes a plurality of slots defining between them a plurality of resilient fastener tabs. Each slot co-operates with an arm of the exhaust casing, which further includes fastener parts attached to the resilient fastening tabs.Type: GrantFiled: March 28, 2013Date of Patent: September 4, 2018Assignee: SAFRAN NACELLESInventors: Gautier Mecuson, Eric Conete, Benoit Carrere, Eric Philippe
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Patent number: 9267531Abstract: An assembly comprising first and second parts made of composite material held one against the other by at least one fastener system comprising a bolt having a flat head from which there extends a threaded portion, and a nut having a flat head from which there extends a shank including tapping suitable for co-operating with the threaded portion of the bolt. The head of the bolt bears against a countersink formed in the first part. The head of the nut bears against a countersink formed in the second part. The fastener system is suitable, during axial expansion of the fastener system, for causing each head to tilt towards the countersink in which it is housed.Type: GrantFiled: May 28, 2014Date of Patent: February 23, 2016Assignee: HERAKLESInventors: Thomas Revel, Benoit Carrere, Eric Conete, Pierre Camy
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Patent number: 9121428Abstract: The invention relates to an assembly comprising first and second parts made of composite material and held against each other by at least one fastener system comprising a rivet having a flat head from which there extends a shank having an enlarged end, and a washer co-operating with the enlarged end of the shank of the rivet, the head of the rivet bearing against a countersink formed in the first part, the washer bearing against the second part. On its face remote from its face bearing against the second part, the washer presents a portion of conical shape. The washer also has a central countersink with the enlarged end of the shank of the rivet pressing thereagainst.Type: GrantFiled: June 18, 2014Date of Patent: September 1, 2015Assignee: HERAKLESInventors: Thomas Revel, Benoit Carrere, Gautier Mecuson
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Publication number: 20150083822Abstract: The invention relates to an aeroengine after-body assembly comprising an exhaust casing made of metal having a plurality of arms extending radially between an inner shroud and an outer shroud. The assembly comprises at least one axisymmetric part made of composite material extending between an upstream end fastened to said exhaust casing and a downstream end that is free. In accordance with the invention, the axisymmetric part has an annular portion at its upstream end, which annular portion includes a plurality of slots defining between them a plurality of resilient fastener tabs. Each slot co-operates with an arm of the exhaust casing, which further includes fastener parts attached to the resilient fastening tabs.Type: ApplicationFiled: March 28, 2013Publication date: March 26, 2015Inventors: Gautier Mecuson, Eric Conete, Benoit Carrere, Eric Philippe
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Publication number: 20140369785Abstract: The invention relates to an assembly comprising first and second parts made of composite material and held against each other by at least one fastener system comprising a rivet having a flat head from which there extends a shank having an enlarged end, and a washer co-operating with the enlarged end of the shank of the rivet, the head of the rivet bearing against a countersink formed in the first part, the washer bearing against the second part. On its face remote from its face bearing against the second part, the washer presents a portion of conical shape. The washer also has a central countersink with the enlarged end of the shank of the rivet pressing thereagainst.Type: ApplicationFiled: June 18, 2014Publication date: December 18, 2014Inventors: Thomas REVEL, Benoit CARRERE, Gautier MECUSON
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Publication number: 20140356094Abstract: An assembly comprising first and second parts made of composite material held one against the other by at least one fastener system comprising a bolt having a flat head from which there extends a threaded portion, and a nut having a flat head from which there extends a shank including tapping suitable for co-operating with the threaded portion of the bolt. The head of the bolt bears against a countersink formed in the first part. The head of the nut bears against a countersink formed in the second part. The fastener system is suitable, during axial expansion of the fastener system, for causing each head to tilt towards the countersink in which it is housed.Type: ApplicationFiled: May 28, 2014Publication date: December 4, 2014Applicant: HERAKLESInventors: Thomas REVEL, Benoit CARRERE, Eric CONETE, Pierre CAMY
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Patent number: 8590316Abstract: The invention relates to a mixer (100) for a separate-stream nozzle of a turbojet, the mixer being designed to mix a hot inner stream from the combustion chamber of the turbojet with a cold outer stream from the fan of the turbojet. The mixer comprises an inner shroud (120) defining a flow channel for said hot inner stream, an outer shroud (110) disposed around the inner shroud (120) and co-operating therewith to define a flow channel for said cold outer stream, and a lobed structure (130) having lobes (1321, 1322) extending longitudinally from the trailing edges (110a, 120a) of said shrouds. The lobed structure (130) is made of a ceramic matrix composite material and is attached to the outer shroud (110) by flexible fastener tabs (140).Type: GrantFiled: April 8, 2008Date of Patent: November 26, 2013Assignee: SNECMA Propulsion SolideInventors: Eric Conete, Benoît Carrere, Laurent Baroumes
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Patent number: 8146372Abstract: An annular combustion chamber has an inner wall and an outer wall of ceramic matrix composite material, together with a chamber end wall that is connected to the inner and outer walls. Elastically-deformable link elements connect the inner wall and the outer chamber walls to inner and outer metal casings. Each of the inner and outer chamber walls is subdivided circumferentially into adjacent sectors along longitudinal edges, each sector extending continuously from the end wall to the opposite end of the chamber and being folded outwards from the chamber at each of its longitudinal edges to form a portion having a U-shaped cross-section terminated by a folded-back margin that is spaced apart from the outer face of the corresponding chamber wall. The link elements are connected to the inner and outer chamber walls by being fastened to the sector margins.Type: GrantFiled: April 1, 2009Date of Patent: April 3, 2012Assignee: Snecma Propulsion SolideInventors: Benoit Carrere, Georges Habarou, Patrick Spriet, Pierre Camy
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Publication number: 20120073306Abstract: An assembled annular combustion chamber comprises an annular inner wall and an annular outer wall made of ceramic matrix composite material together with a chamber end wall connected to the inner and outer walls and provided with orifices for receiving injectors. Elastically-deformable link parts connect the inner wall and the outer wall of the chamber to inner and outer casings that are made of metal. The assembly formed by the inner wall, the outer wall, and the combustion chamber end wall is subdivided circumferentially into adjacent chamber sectors, each sector being made as a single piece of ceramic composite material and comprising an inner wall sector, an outer wall sector, and a chamber end wall sector. The link parts connect the inner metal casing and the outer metal casing respectively to each inner wall sector of the combustion chamber and to each outer wall sector of the chamber. The chamber end wall sectors are in contact with a one-piece ring to which they are connected.Type: ApplicationFiled: April 1, 2009Publication date: March 29, 2012Applicant: SNECMA PROPULSION SOLIDEInventors: Georges Habarou, Pierre Camy, Benoit Carrere, Eric Bouillon
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Patent number: 8141371Abstract: An assembled annular combustion chamber comprises an annular inner wall and an annular outer wall made of ceramic matrix composite material together with a chamber end wall connected to the inner and outer walls and provided with orifices for receiving injectors. Elastically-deformable link parts connect the inner wall and the outer wall of the chamber to inner and outer casings that are made of metal. The assembly formed by the inner wall, the outer wall, and the combustion chamber end wall is subdivided circumferentially into adjacent chamber sectors, each sector being made as a single piece of ceramic composite material and comprising an inner wall sector, an outer wall sector, and a chamber end wall sector. The link parts connect the inner metal casing and the outer metal casing respectively to each inner wall sector of the combustion chamber and to each outer wall sector of the chamber. The chamber end wall sectors are in contact with a one-piece ring to which they are connected.Type: GrantFiled: April 1, 2009Date of Patent: March 27, 2012Assignee: Snecma Propulsion SolideInventors: Georges Habarou, Pierre Camy, Benoit Carrere, Eric Bouillon
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Publication number: 20100126183Abstract: The invention relates to a mixer (100) for a separate-stream nozzle of a turbojet, the mixer being designed to mix a hot inner stream from the combustion chamber of the turbojet with a cold outer stream from the fan of the turbojet. The mixer comprises an inner shroud (120) defining a flow channel for said hot inner stream, an outer shroud (110) disposed around the inner shroud (120) and co-operating therewith to define a flow channel for said cold outer stream, and a lobed structure (130) having lobes (1321, 1322) extending longitudinally from the trailing edges (110a, 120a) of said shrouds. The lobed structure (130) is made of a ceramic matrix composite material and is attached to the outer shroud (110) by flexible fastener tabs (140).Type: ApplicationFiled: April 8, 2008Publication date: May 27, 2010Applicant: SNECMA PROPULSION SOLIDEInventors: Eric Conete, Benoît Carrere, Laurent Baroumes
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Publication number: 20090249790Abstract: An annular combustion chamber has an inner wall and an outer wall of ceramic matrix composite material, together with a chamber end wall that is connected to the inner and outer walls. Elastically-deformable link elements connect the inner wall and the outer chamber walls to inner and outer metal casings. Each of the inner and outer chamber walls is subdivided circumferentially into adjacent sectors along longitudinal edges, each sector extending continuously from the end wall to the opposite end of the chamber and being folded outwards from the chamber at each of its longitudinal edges to form a portion having a U-shaped cross-section terminated by a folded-back margin that is spaced apart from the outer face of the corresponding chamber wall. The link elements are connected to the inner and outer chamber walls by being fastened to the sector margins.Type: ApplicationFiled: April 1, 2009Publication date: October 8, 2009Applicant: SNECMA PROPULISION SOLIDEInventors: Benoit Carrere, Georges Habarou, Patrick Spriet, Pierre Camy