Patents by Inventor Philippe Verseux
Philippe Verseux 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: 20230228201Abstract: An annular intermediate casing for a turbomachine through which an aerodynamic airstream circulates, including a radially internal shroud (31), a radially external shroud, at least one stator blade including a vane with a leading edge, and at least one aero-dynamic member which is formed of a structural arm extending radially at least in part between the radially internal shroud and the radially external shroud. The aerodynamic member includes a leading edge which is aligned with the leading edge of the stator blade in one plane and which is borne by a profiled portion positioned upstream of the structural arm in the direction of circulation of the aerodynamic airstream, the profiled portion, the structural arm, the radially internal shroud and the radially external shroud being monobloc.Type: ApplicationFiled: April 22, 2021Publication date: July 20, 2023Inventors: Frederic Jacques Eugene GOUPIL, Francois Marie Paul MARLIN, Kaelig Merwen ORIEUX, Philippe VERSEUX, Yacine CHERAGA
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Patent number: 9545762Abstract: A coupling made of composite material including a polymer matrix reinforced by a fiber structure is disclosed. The coupling includes a structural portion reinforced by a main fiber structure, and a first machining portion reinforced by a first fiber structure that is distinct from the main fiber structure. The matrices of the structural portion and of the first machining portion are identical. The first machining portion is situated on at least a fraction of the main face of the structural portion and is machined in a first machining surface. There is no intersection between the first machining surface and the fibers of the main fiber structure.Type: GrantFiled: March 25, 2013Date of Patent: January 17, 2017Assignee: SNECMAInventors: Francois Marie Paul Marlin, Philippe Verseux
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Patent number: 9017021Abstract: An aeroengine fan casing is made of composite material including fiber reinforcement densified by a matrix. The casing is secured to at least one ring or ring sector that is situated on the inside face of the casing and that is mechanically connected to an equipment fastener part that is situated on the outside face of the casing, in particular for fastening an accessory gearbox.Type: GrantFiled: October 20, 2011Date of Patent: April 28, 2015Assignee: SnecmaInventors: Philippe Verseux, Regis Eugene Henri Servant
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Patent number: 8876467Abstract: An inner wall for a nacelle of a turbomachine, the inner wall including an outer annular fan casing for surrounding the fan blades and including at its upstream end a flange for fastening to a ring in axial alignment therewith, and a soundproofing inner annular structure for extending upstream from the fan blades, the fan casing extending substantially as far as an upstream end of the soundproofing structure such that the upstream flange of the fan casing is situated in a vicinity of the upstream end of the soundproofing structure.Type: GrantFiled: July 15, 2009Date of Patent: November 4, 2014Assignee: SNECMAInventors: Georges Jean Xavier Riou, Philippe Verseux
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Patent number: 8740568Abstract: A turbomachine fan rotor including a disk carrying blades with roots that are engaged in axial grooves of the disk, a spacer being interposed between the bottom of each groove and the corresponding blade root, the spacer including at its upstream end a nib for retaining the blade root, the nib including a downstream abutment face against which the upstream end of the blade root bears in event of a violent force being applied thereto, the abutment face being oblique relative to the axis of rotation of the rotor.Type: GrantFiled: March 27, 2009Date of Patent: June 3, 2014Assignee: SNECMAInventors: Xavier Louis Barthelemy Millier, Régis Eugène Henri Servant, Philippe Verseux
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Patent number: 8424921Abstract: A coupling made of composite material including a polymer matrix reinforced by a fiber structure is disclosed. The coupling includes a structural portion reinforced by a main fiber structure, and a first machining portion reinforced by a first fiber structure that is distinct from the main fiber structure. The matrices of the structural portion and of the first machining portion are identical. The first machining portion is situated on at least a fraction of the main face of the structural portion and is machined in a first machining surface, and there is no intersection between the first machining surface and the fibers of the main fiber structure.Type: GrantFiled: December 12, 2008Date of Patent: April 23, 2013Assignee: SNECMAInventors: Francois Marie Paul Marlin, Philippe Verseux
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Patent number: 8322971Abstract: A composite material casing of varying thickness, in particular for a gas turbine fan, is made by forming fiber reinforcement and densifying the reinforcement with a matrix. The fiber reinforcement is made by winding superposed layers of a fiber texture onto a mandrel, the texture being made by three-dimensional weaving with varying thickness.Type: GrantFiled: February 19, 2008Date of Patent: December 4, 2012Assignee: SNECMAInventors: Dominique Coupe, Bruno Jacques Gerard Dambrine, Francois Marie Paul Marlin, Olivier Michael Molinari, Antoine Phelippeau, Philippe Verseux
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Publication number: 20120099981Abstract: An aeroengine fan casing is made of composite material comprising fiber reinforcement densified by a matrix. The casing (10) is secured to at least one ring (24) or ring sector that is situated on the inside face of the casing and that is mechanically connected to an equipment fastener part (26) that is situated on the outside face of the casing, in particular for fastening an accessory gearbox.Type: ApplicationFiled: October 20, 2011Publication date: April 26, 2012Applicant: SNECMAInventors: Philippe VERSEUX, Régis Eugéne Henri Servant
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Patent number: 8061967Abstract: A panel for supporting abradable material in a turbojet, the panel comprising a rigid support for fastening to an inside wall of a fan casing and having one face covered in a laminated structure carrying a layer of abradable material, the laminated structure comprising sheets of fibers embedded in a polymer, and comprising an upstream portion covered by the abradable material and a downstream portion that extends beyond the abradable material, the thickness of the downstream portion being greater than the thickness of the upstream portion and being capable of withstanding ice impacts.Type: GrantFiled: December 8, 2008Date of Patent: November 22, 2011Assignee: SnecmaInventors: Francois Marie Paul Marlin, Philippe Verseux
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Patent number: 8038386Abstract: The present invention relates to an intermediate casing of a turbojet comprising, between an inner hub and an outer cylindrical shroud, a plurality of radial arms at least one of which is hollow, a radial transmission shaft for driving the auxiliary machines being mounted rotatably in said radial arm, a first end of the transmission shaft passing through the inner hub and the second end passing through the outer cylindrical shroud. The housing is notable in that the inner volume consists of a single compartment housing the transmission shaft and forming a passageway for a lubrication fluid.Type: GrantFiled: October 3, 2008Date of Patent: October 18, 2011Assignee: SNECMAInventors: Thierry François Maurice Duchatelle, Philippe Verseux
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Publication number: 20110150657Abstract: A turbomachine fan rotor including a disk carrying blades with roots that are engaged in axial grooves of the disk, a spacer being interposed between the bottom of each groove and the corresponding blade root, the spacer including at its upstream end a nib for retaining the blade root, the nib including a downstream abutment face against which the upstream end of the blade root bears in event of a violent force being applied thereto, the abutment face being oblique relative to the axis of rotation of the rotor.Type: ApplicationFiled: March 27, 2009Publication date: June 23, 2011Applicant: SNECMAInventors: Xavier Louis Barthelemy Millier, Regis Eugene Henri Servant, Philippe Verseux
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Publication number: 20110142615Abstract: An inner wall for a nacelle of a turbomachine, the inner wall including an outer annular fan casing for surrounding the fan blades and including at its upstream end a flange for fastening to a ring in axial alignment therewith, and a soundproofing inner annular structure for extending upstream from the fan blades, the fan casing extending substantially as far as an upstream end of the soundproofing structure such that the upstream flange of the fan casing is situated in a vicinity of the upstream end of the soundproofing structure.Type: ApplicationFiled: July 15, 2009Publication date: June 16, 2011Applicant: SNECMAInventors: Georges Jean Xavier Riou, Philippe Verseux
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Publication number: 20100329843Abstract: A panel for supporting abradable material in a turbojet, the panel comprising a rigid support for fastening to an inside wall of a fan casing and having one face covered in a laminated structure carrying a layer of abradable material, the laminated structure comprising sheets of fibers embedded in a polymer, and comprising an upstream portion covered by the abradable material and a downstream portion that extends beyond the abradable material, the thickness of the downstream portion being greater than the thickness of the upstream portion and being capable of withstanding ice impacts.Type: ApplicationFiled: December 8, 2008Publication date: December 30, 2010Applicant: SNECMAInventors: Francois Marie Paul MARLIN, Philippe Verseux
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Publication number: 20090200700Abstract: The invention relates to a coupling made of composite material comprising a polymer matrix reinforced by a fiber structure. The coupling comprises a structural portion reinforced by a main fiber structure, and a first machining portion reinforced by a first fiber structure that is distinct from the main fiber structure, the matrices of the structural portion and of the first machining portion being identical, the first machining portion being situated on at least a fraction of the main face of the structural portion and being machined in a first machining surface, there being no intersection between the first machining surface and the fibers of the main fiber structure.Type: ApplicationFiled: December 12, 2008Publication date: August 13, 2009Applicant: SNECMAInventors: Francois Marie Paul Marlin, Philippe Verseux
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Publication number: 20080206048Abstract: A composite material casing of varying thickness, in particular for a gas turbine fan, is made by forming fiber reinforcement and densifying the reinforcement with a matrix. The fiber reinforcement is made by winding superposed layers of a fiber texture onto a mandrel, the texture being made by three-dimensional weaving with varying thickness.Type: ApplicationFiled: February 19, 2008Publication date: August 28, 2008Applicant: SNECMAInventors: Dominique Coupe, Bruno Jacques Gerard Dambrine, Francois Marie Paul Marlin, Olivier Michael Molinari, Antoine Phelippeau, Philippe Verseux