Patents by Inventor Philippe Gerard Edmond Joly
Philippe Gerard Edmond Joly 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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Patent number: 11885268Abstract: An assembly for a turbine engine extending along an axis, includes a stator, a low-pressure compressor shaft, a low-pressure compressor comprising a rotor comprising a drum rotatably coupled to the shaft of the low-pressure compressor, and a fan comprising a disk rotatably coupled to the shaft of the low-pressure compressor. The drum has a radially internal part rotatably coupled to the shaft of the low-pressure compressor and a radially external part fixed to the radially internal part by means of detachable fixing means. A first axial retention means is configured to axially and detachably retain the disk of the fan relative to the shaft of the low-pressure compressor. A second axial retention means is configured to axially and detachably retain the radially internal part of the drum relative to the shaft of the low-pressure compressor.Type: GrantFiled: January 6, 2021Date of Patent: January 30, 2024Assignee: SAFRAN AIRCRAFT ENGINESInventors: Philippe Gérard Edmond Joly, Jean-Marc Claude Perrollaz, Laurent Jablonski
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Patent number: 11828191Abstract: A turbomachine assembly includes a casing, first and second rotors, and a damper. The first rotor includes a disk and blades and is movable in rotation relative to the casing. The second rotor is movable relative to the casing around a longitudinal axis. The damper damps a movement of the first rotor relative to the second rotor. The damper includes first to third parts. The first part bears on the first rotor in a first area extending over a first angular sector around the longitudinal axis and applies a first centrifugal force on the first rotor. The second part bears on the first rotor in a second area that is smaller than the first angular sector and extends over a second angular sector around the longitudinal axis. The third part bears on the second rotor and applies a second centrifugal force on the second rotor.Type: GrantFiled: May 27, 2020Date of Patent: November 28, 2023Assignee: SAFRAN AIRCRAFT ENGINESInventors: Philippe Gérard Edmond Joly, Romain Nicolas Lagarde, Jean-Marc Claude Perrollaz, Laurent Jablonski, François Jean Comin, Edouard Antoine Dominique Marie De Jaeghere, Charles Jean-Pierre Douguet
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Patent number: 11808170Abstract: The present invention relates to a turbomachine assembly, comprising: a casing (10), a first rotor (12) which is movable in rotation with respect to the casing (10) about a longitudinal axis (X-X), and comprising: *a disk (120), and *a plurality of blades (122) capable of flapping with respect to the disk (120) during a rotation of the first rotor (12) with respect to the casing (10), a second rotor (140) which is movable in rotation with respect to the casing (10) about the longitudinal axis (X-X), and a damper (2) which is configured to damp a displacement of the first rotor (12) with respect to the second rotor (140) in a plane orthogonal to the longitudinal axis (X-X), the displacement being caused by a flapping of at least one blade (122) among the plurality of blades (122), the damper (2) comprising: o a first bearing part (21): *bearing against the first rotor (12), and *being configured to apply a first centrifugal force (C1) to the first rotor (12), o a second bearing part (22): *bearing against theType: GrantFiled: May 27, 2020Date of Patent: November 7, 2023Assignee: SAFRAN AIRCRAFT ENGINESInventors: Philippe Gérard Edmond Joly, Romain Nicolas Lagarde, Jean-Marc Claude Perrollaz, Laurent Jablonski, François Jean Comin, Edouard Antoine Dominique Marie De Jaeghere, Charles Jean-Pierre Douguet
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Patent number: 11808169Abstract: The present invention relates to an assembly for a turbomachine, comprising: a first rotor; a second rotor, and a damper (2) configured to damp a displacement of the first rotor relative to the second rotor, the damper comprising: a first portion (21) bearing against the first rotor and having a first thickness, a second portion (22) bearing against the second rotor and having a second radial thickness, and a third portion (23) connecting the first portion (21) to the second portion (22) and having a third radial thickness, wherein the third radial thickness is greater than at least one of the first radial thickness and the second radial thickness.Type: GrantFiled: May 27, 2020Date of Patent: November 7, 2023Assignee: SAFRAN AIRCRAFT ENGINESInventors: Philippe Gérard Edmond Joly, Romain Nicolas Lagarde, Jean-Marc Claude Perrollaz, Laurent Jablonski, François Jean Comin, Edouard Antoine Dominique Marie De Jaeghere, Charles Jean-Pierre Douguet
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Patent number: 11585229Abstract: The invention relates to a bladed disk (1) of a fan, comprising: a hub (10) comprising an outer radial platform (13) designed so as to define an inner gas flow stream in the turbomachine, a plurality of blades (20) comprising a root (23) connected to the platform (13), a leading edge (21) and a trailing edge (22), a groove formed in the platform (13) around part of the root (23) of each blade (20) in an area adjacent to the leading edge (21) and/or the trailing edge (22), and a joint (30) placed in the groove (15) in such a way that it extends in the extension of the radially outer face (14) of the platform (13) in order to ensure a continuity of the inner flow stream.Type: GrantFiled: March 19, 2019Date of Patent: February 21, 2023Assignee: SAFRAN AIRCRAFT ENGINESInventors: Laurent Jablonski, François Jean Comin, Philippe Gérard Edmond Joly, Jean-Marc Claude Perrollaz, Anthony Lafitte, Rémi Roland Robert Mercier
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Publication number: 20230038378Abstract: An assembly for a turbine engine extending along an axis, includes a stator, a low-pressure compressor shaft, a low-pressure compressor comprising a rotor comprising a drum rotatably coupled to the shaft of the low-pressure compressor, and a fan comprising a disk rotatably coupled to the shaft of the low-pressure compressor. The drum has a radially internal part rotatably coupled to the shaft of the low-pressure compressor and a radially external part fixed to the radially internal part by means of detachable fixing means. A first axial retention means is configured to axially and detachably retain the disk of the fan relative to the shaft of the low-pressure compressor. A second axial retention means is configured to axially and detachably retain the radially internal part of the drum relative to the shaft of the low-pressure compressor.Type: ApplicationFiled: January 6, 2021Publication date: February 9, 2023Applicant: SAFRAN AIRCRAFT ENGINESInventors: Philippe Gérard Edmond JOLY, Jean-Marc Claude PERROLLAZ, Laurent JABLONSKI
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Patent number: 11536157Abstract: The invention relates to an assembly (1) for a turbomachine comprising: a first rotor module (2) comprising a first blade (20), a second rotor module (3), connected to the first rotor module (2), and comprising a second blade with a length less than the first blade (20), and a damping device (4) extending with at least one component along a turbomachine longitudinal axis (X-X), characterized in that the damping device (4) is annular while extending circumferentially around the turbomachine longitudinal axis (X-X) and in that the damping device (4) comprises a first radial external surface (40) supported with friction against the first module (2) as well as a second radial external surface (42) supported with friction against the second module (3), so as to couple the modules (2, 3) in order to damp their respective vibrational movements during operation.Type: GrantFiled: December 18, 2018Date of Patent: December 27, 2022Assignee: SAFRAN AIRCRAFT ENGINESInventors: Philippe Gérard Edmond Joly, François Jean Comin, Charles Jean-Pierre Douguet, Laurent Jablonski, Romain Nicolas LaGarde, Jean-Marc Claude Perrollaz
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Patent number: 11466571Abstract: A turbomachine assembly is provided. The assembly includes: a first rotor module including a first blade, a second rotor module, connected to the first rotor module, and including a second blade of smaller length than the first blade, and a damping device including a plurality of first radial external surfaces supported with friction against the first module. The damping device is stepped, and includes a second radial external surface supported with friction against the second module, so as to couple the modules for the purpose of damping their respective vibrational movements during operation.Type: GrantFiled: December 17, 2018Date of Patent: October 11, 2022Assignee: Safran Aircraft EnginesInventors: Philippe Gerard Edmond Joly, Marie-Oceane Parent, Francois Jean Comin, Romain Nicolas Lagarde, Jean-Marc Claude Perrollaz, Laurent Jablonski, Charles Jean-Pierre Douguet
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Publication number: 20220299040Abstract: A turbomachine assembly is provided. The assembly includes: a first rotor module including a first blade, a second rotor module, connected to the first rotor module, and including a second blade of smaller length than the first blade, and a damping device including a plurality of first radial external surfaces supported with friction against the first module. The damping device is stepped, and includes a second radial external surface supported with friction against the second module, so as to couple the modules for the purpose of damping their respective vibrational movements during operation.Type: ApplicationFiled: December 17, 2018Publication date: September 22, 2022Applicant: Safran Aircraft EnginesInventors: Philippe Gerard Edmond JOLY, Marie-Oceane PARENT, Francois Jean COMIN, Romain Nicolas LAGARDE, Jean-Marc Claude PERROLLAZ, Laurent JABLONSKI, Charles Jean-Pierre DOUGUET
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Patent number: 11421534Abstract: An assembly for a turbomachine including a first rotor module (2) with a first blade (20), and a second rotor module (3), connected to the first rotor module (2). The second rotor module includes a second blade with a smaller length than the first blade (20). A damping device (4) is attached to the second rotor module (3) and includes a radial external surface (40) supported with friction against the first module (2), so as to couple the modules (2, 3) for the purpose of damping their respective vibrational movements during operation.Type: GrantFiled: December 14, 2018Date of Patent: August 23, 2022Assignee: SAFRAN AIRCRAFT ENGINESInventors: Philippe Gerard Edmond Joly, Francois Jean Comin, Laurent Jablonski, Romain Nicolas Lagarde, Jean-Marc Claude Perrollaz
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Publication number: 20220228495Abstract: The present invention relates to a turbomachine assembly, comprising: a casing (10), a first rotor (12) which is movable in rotation with respect to the casing (10) about a longitudinal axis (X-X), and comprising: *a disk (120), and *a plurality of blades (122) capable of flapping with respect to the disk (120) during a rotation of the first rotor (12) with respect to the casing (10), a second rotor (140) which is movable in rotation with respect to the casing (10) about the longitudinal axis (X-X), and a damper (2) which is configured to damp a displacement of the first rotor (12) with respect to the second rotor (140) in a plane orthogonal to the longitudinal axis (X-X), the displacement being caused by a flapping of at least one blade (122) among the plurality of blades (122), the damper (2) comprising: o a first bearing part (21): *bearing against the first rotor (12), and *being configured to apply a first centrifugal force (C1) to the first rotor (12), o a second bearing part (22): *bearing against theType: ApplicationFiled: May 27, 2020Publication date: July 21, 2022Applicant: SAFRAN AIRCRAFT ENGINESInventors: Philippe Gérard Edmond JOLY, Romain Nicolas LAGARDE, Jean-Marc Claude PERROLLAZ, Laurent JABLONSKI, François Jean COMIN, Edouard Antoine Dominique Marie DE JAEGHERE, Charles Jean-Pierre DOUGUET
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Publication number: 20220228491Abstract: A turbomachine assembly includes a casing, first and second rotors, and a damper. The first rotor includes a disk and blades and is movable in rotation relative to the casing. The second rotor is movable relative to the casing around a longitudinal axis. The damper damps a movement of the first rotor relative to the second rotor. The damper includes first to third parts. The first part bears on the first rotor in a first area extending over a first angular sector around the longitudinal axis and applies a first centrifugal force on the first rotor. The second part bears on the first rotor in a second area that is smaller than the first angular sector and extends over a second angular sector around the longitudinal axis. The third part bears on the second rotor and applies a second centrifugal force on the second rotor.Type: ApplicationFiled: May 27, 2020Publication date: July 21, 2022Applicant: SAFRAN AIRCRAFT ENGINESInventors: Philippe Gérard Edmond JOLY, Romain Nicolas LAGARDE, Jean-Marc Claude PERROLLAZ, Laurent JABLONSKI, François Jean COMIN, Edouard Antoine Dominique Marie DE JAEGHERE, Charles Jean-Pierre DOUGUET
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Publication number: 20220228494Abstract: The present invention reltues to an assembly Ru a turbomachine, comprising: a first rotor; a second rotor, and, a damper (2) configured to damp a displacement of the first rotor relative to the second rotor, the damper comprising: a first portion (21) bearing against the first rotor and having a first thickness, a second portion (22) bearing against the second rotor and having a second radial thickness, and a third portion (23) connecting the first portion (21) to the second portion (22) and having a third radial thickness, wherein the third radial thickness is greater than at least one of the first radial thickness and the second radial thickness.Type: ApplicationFiled: May 27, 2020Publication date: July 21, 2022Applicant: SAFRAN AIRCRAFT ENGINESInventors: Philippe Gérard Edmond JOLY, Romain Nicolas LAGARDE, Jean-Marc Claude PERROLLAZ, Laurent JABLONSKI, François Jean COMIN, Edouard Antoine Dominique DE JAEGHERE, Charles Jean-Pierre DOUGUET
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Patent number: 11346233Abstract: The invention relates to a turbomachine assembly (1) comprising: a first rotor module (2) comprising a first blade (20), a second rotor module (3), connected to the first rotor module (2), and comprising a second blade of smaller length than the first blade (20), and a damping device (4) comprising a first radial external surfaces (41) supported with friction against the first module (2), as well as a second radial external surface (42) supported with friction against the second module (3), so as to couple the modules (2, 3) for the purpose of damping their respective vibrational movements during operation.Type: GrantFiled: December 14, 2018Date of Patent: May 31, 2022Assignee: SAFRAN AIRCRAFT ENGINESInventors: Philippe Gérard Edmond Joly, François Jean Comin, Charles Jean-Pierre Douguet, Laurent Jablonski, Romain Nicolas Lagarde, Jean Marc Claude Perrollaz
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Patent number: 11209012Abstract: The invention proposes a fan, in particular for a turbomachine of small size such as a jet engine, having a hub ratio which corresponds to the ratio of the diameter of the inner limit of the incoming air stream at the radially inner ends of the leading edges of the fan blades, divided by the diameter of the circle around which the outer ends of the fan blades pass, having a value of between 0.20 and 0.265.Type: GrantFiled: April 24, 2019Date of Patent: December 28, 2021Assignee: Safran Aircraft EnginesInventors: Laurent Jablonski, Philippe Gérard Edmond Joly, Christophe Perdrigeon, Damien Merlot, Hervé Pohier
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Publication number: 20210079794Abstract: The invention relates to a turbomachine assembly (1) comprising: a first rotor module (2) comprising a first blade (20), a second rotor module (3), connected to the first rotor module (2), and comprising a second blade of smaller length than the first blade (20), and a damping device (4) comprising a first radial external surfaces (41) supported with friction against the first module (2), as well as a second radial external surface (42) supported with friction against the second module (3), so as to couple the modules (2, 3) for the purpose of damping their respective vibrational movements during operation.Type: ApplicationFiled: December 14, 2018Publication date: March 18, 2021Applicant: SAFRAN AIRCRAFT ENGINESInventors: Philippe Gérard Edmond JOLY, François Jean COMIN, Charles Jean-Pierre DOUGUET, Laurent JABLONSKI, Romain Nicolas LAGARDE, Jean Marc Claude PERROLLAZ
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Patent number: 10927683Abstract: The invention relates to a turbomachine assembly (1) comprising: a first rotor module (2) comprising a disk (21), a first blade (20) being mounted on the external periphery of the disk (21), the first blade (20) comprising a platform (25) and a support (27), a second rotor module (3), connected to the first rotor module (2) by means of at least two attachments (22) and comprising a second blade of smaller length than the first blade (20), and a damping device (4) attached to the attachment (22) between the first (2) and the second (3) rotor module so as to dampen their vibrational movements during operation, and comprising: a head (40) comprising a first radial external surface (42) supported with friction against the platform (25), and two attachment feet (41) extending on either side of the support (27) of the first blade (20).Type: GrantFiled: December 13, 2018Date of Patent: February 23, 2021Assignee: SAFRAN AIRCRAFT ENGINESInventors: Philippe Gerard Edmond Joly, Francois Jean Comin, Laurent Jablonski, Romain Nicolas Lagarde, Jean-Marc Claude Perrollaz, Charles Jean-Pierre Douguet
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Publication number: 20210025283Abstract: The invention relates to a bladed disk (1) of a fan, comprising: a hub (10) comprising an outer radial platform (13) designed so as to define an inner gas flow stream in the turbomachine, a plurality of blades (20) comprising a root (23) connected to the platform (13), a leading edge (21) and a trailing edge (22), a groove formed in the platform (13) around part of the root (23) of each blade (20) in an area adjacent to the leading edge (21) and/or the trailing edge (22), and a joint (30) placed in the groove (15) in such a way that it extends in the extension of the radially outer face (14) of the platform (13) in order to ensure a continuity of the inner flow stream.Type: ApplicationFiled: March 19, 2019Publication date: January 28, 2021Applicant: SAFRAN AIRCRAFT ENGINESInventors: Laurent JABLONSKI, François Jean COMIN, Philippe Gérard Edmond JOLY, Jean-Marc Claude PERROLLAZ, Anthony LAFITTE, Rémi Roland Robert MERCIER
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Publication number: 20210010391Abstract: The invention relates to an assembly (1) for a turbomachine comprising: a first rotor module (2) comprising a first blade (20), a second rotor module (3), connected to the first rotor module (2), and comprising a second blade with a length less than the first blade (20), and a damping device (4) extending with at least one component along a turbomachine longitudinal axis (X-X), characterized in that the damping device (4) is annular while extending circumferentially around the turbomachine longitudinal axis (X-X) and in that the damping device (4) comprises a first radial external surface (40) supported with friction against the first module (2) as well as a second radial external surface (42) supported with friction against the second module (3), so as to couple the modules (2, 3) in order to damp their respective vibrational movements during operation.Type: ApplicationFiled: December 18, 2018Publication date: January 14, 2021Applicant: Safran Aircraft EnginesInventors: Philippe Gérard Edmond JOLY, François Jean COMIN, Charles Jean-Pierre DOUGUET, Laurent JABLONSKI, Romain Nicolas LAGARDE, Jean-Marc Claude PERROLLAZ
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Patent number: 10634158Abstract: The invention relates to a blade, the platform (14) of which has at least one bumper (40) which rises, on the inner face, from a connection to an intermediate area of the blade located along a longitudinal axis of the blade, between the blade root and the outer face (143), towards a free side edge (145) of the platform. The platform bumper (40) locally has a thinned portion at a distance from said free side edge of the platform. The invention is applicable to turboshaft engine fans.Type: GrantFiled: September 3, 2015Date of Patent: April 28, 2020Assignee: Safran Aircraft EnginesInventors: Philippe Gérard Edmond Joly, Damien Merlot, Jean-Marc Claude Perrollaz