Patents by Inventor Romain Nicolas LAGARDE
Romain Nicolas LAGARDE 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: 11952950Abstract: An axial turbomachine comprising a compression device with a variable-orientation vane rectifier stage; a combustion chamber downstream of the compression device; a turbine device downstream of the combustion chamber; and a leak passage of air compressed by the compression device, between the compression device and the turbine device for cooling the turbine device; and where the rectifier stage is configured to modulate the section of the leak passage according to the orientation of the vanes of the stage.Type: GrantFiled: July 23, 2020Date of Patent: April 9, 2024Assignee: SAFRAN AIRCRAFT ENGINES SASInventors: Lilian Yann Dumas, Baptiste René Roger Batonnet, Romain Nicolas Lagarde
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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: 11808160Abstract: A sub-assembly of a turbine engine including a shaft, a bearing for guiding an axial end of the shaft, a nut which is screw-connected to the end of the shaft and a member for blocking the rotation of the nut in relation to the end of the shaft, wherein the member for blocking the nut includes a first section bearing a plurality of flexible tabs, one end of each tab of which cooperates with a radially inner annular wall of the end of the shaft and includes a second section which cooperates with the nut, characterised in that the second section of the blocking member is screw-connected to the nut and the features of the thread between the blocking member and the nut are different from the features of the thread between the nut and the end of the shaft.Type: GrantFiled: March 2, 2020Date of Patent: November 7, 2023Assignee: SAFRAN AIRCRAFT ENGINESInventors: Romain Nicolas Lagarde, Marie-Charline Stéphanie Charbonnier, Jean-Marc Claude Perrollaz, Lilian Yann Dumas
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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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Publication number: 20220275762Abstract: An axial turbomachine comprising a compression device with a variable-orientation vane rectifier stage; a combustion chamber downstream of the compression device; a turbine device downstream of the combustion chamber; and a leak passage of air compressed by the compression device, between the compression device and the turbine device for cooling the turbine device; and where the rectifier stage is configured to modulate the section of the leak passage according to the orientation of the vanes of the stage.Type: ApplicationFiled: July 23, 2020Publication date: September 1, 2022Inventors: Lilian Yann DUMAS, Baptiste René Roger BATONNET, Romain Nicolas LAGARDE
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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: 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: 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: 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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Publication number: 20220127973Abstract: A sub-assembly of a turbine engine including a shaft, a bearing for guiding an axial end of the shaft, a nut which is screw-connected to the end of the shaft and a member for blocking the rotation of the nut in relation to the end of the shaft, wherein the member for blocking the nut includes a first section bearing a plurality of flexible tabs, one end of each tab of which cooperates with a radially inner annular wall of the end of the shaft and includes a second section which cooperates with the nut, characterised in that the second section of the blocking member is screw-connected to the nut and the features of the thread between the blocking member and the nut are different from the features of the thread between the nut and the end of the shaft.Type: ApplicationFiled: March 2, 2020Publication date: April 28, 2022Inventors: Romain Nicolas LAGARDE, Marie-Charline Stéphanie CHARBONNIER, Jean-Marc Claude PERROLLAZ, Lilian Yann DUMAS
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Patent number: 11208951Abstract: An air bleed device for an aircraft engine, including a frame and a flap able to rotate about an axis in relation to the frame, the device further including a return system configured to bias the flap in a determined position about the axis and including a torsion spring, a first end of which is connected to the flap and a second end of which is connected to the frame. The second end is connected to the frame by adjusting the preload of the spring by screwing when the flap is in the determined position.Type: GrantFiled: March 29, 2019Date of Patent: December 28, 2021Assignee: SAFRAN AIRCRAFT ENGINESInventors: Pascal Xavier Delaitre, Romain Nicolas Lagarde, Jean-Marc Claude Perrollaz, Antonin Etienne Diego Tessiereau
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Patent number: 11053846Abstract: The invention relates to an intermediate housing hub (2) comprising a discharge stream conduit (18) having a given length (L1), and discharge fins (22) extending in the discharge stream conduit (18) and having a given chord length (L2), the chord length (L2) of at least one of the discharge fins (22) being at least equal to 50% of the length of conduit (L1).Type: GrantFiled: December 28, 2017Date of Patent: July 6, 2021Assignee: SAFRAN AIRCRAFT ENGINESInventors: Julien Antoine Henri Jean Szydlowski, Romain Nicolas Lagarde, Ghislain Maxime Romuald Madiot, Benjamin Lukowski
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Patent number: 11041393Abstract: The invention concerns a part of a turbomachine, including an element having a first aerodynamic surface including a counterbore at the bottom of which is provided a mounting hole of a fastening screw of the part, and a washer configured to be accommodate into the counterbore and intended to serve as a support for a head of the fastening screw, wherein the washer has an asymmetry of revolution about a screwing axis and is engaged by shape complementarity in the counterbore, and in that the washer includes a second aerodynamic surface extending in the continuity of the first surface.Type: GrantFiled: June 6, 2019Date of Patent: June 22, 2021Assignee: SAFRAN AIRCRAFT ENGINESInventors: Romain Nicolas Lagarde, Marie-Charline Stephanie Charbonnier, Jean-Marc Claude Perrollaz
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Patent number: 11015477Abstract: An assembly for the control of variable pitch blades. The assembly includes a movable part movable parallel to an axis is in engagement with pivot connections which rotate about at least one radial axis fixed with respect to the casing, and which act on a radial shaft, which passes through a clevis fixed with a control ring to rotate with it about said axis. The radial shaft is mounted radially rotating with respect to the control ring and the casing.Type: GrantFiled: June 21, 2019Date of Patent: May 25, 2021Assignee: Safran Aircraft EnginesInventors: Romain Nicolas Lagarde, Lilian Yann Dumas
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Patent number: 10975720Abstract: The invention relates to a balancing system of an aircraft turbomachine comprising a first annular row of first mounting ports for mounting balancing members, and a second annular row of second mounting ports for mounting balancing members which is axially offset from the first annular row, the number and angular positions of the first mounting ports being identical to the number and angular positions of the second mounting ports.Type: GrantFiled: July 31, 2019Date of Patent: April 13, 2021Assignee: SAFRAN AIRCRAFT ENGINESInventors: Nadège Pauline Audrey Hugon, Thomas Giraudeau, Jean-Marc Claude Perrollaz, Baptiste René Roger Batonnet, Romain Nicolas Lagarde