Patents by Inventor Charles Jean
Charles Jean 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: 11990119Abstract: An interactive system may be implemented in part by an audio device located within a user environment, which may accept speech commands from a user and may also interact with the user by means of generated speech. In order to improve performance of the interactive system, a user may use a separate device, such as a personal computer or mobile device, to access a graphical user interface that lists details of historical speech interactions. The graphical user interface may be configured to allow the user to provide feedback and/or corrections regarding the details of specific interactions.Type: GrantFiled: March 8, 2021Date of Patent: May 21, 2024Assignee: Amazon Technologies, Inc.Inventors: Gilles Jean Roger Belin, Charles S. Rogers, III, Robert David Owen, Jeffrey Penrod Adams, Rajiv Ramachandran, Gregory Michael Hart
-
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
-
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
-
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
-
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
-
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
-
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
-
Patent number: 11441442Abstract: A sealing device between a rotor part and a stator part, including at least one abradable coating cooperating with at least two upstream and downstream labyrinth seal lips. Axially upstream of the labyrinth seal lips, the sealing device includes a circumferential wall that radially extends beyond the upstream free axial sealing surface of the coating to create, at the free end of the upstream labyrinth seal lip, a separation of the circulating gas.Type: GrantFiled: April 24, 2018Date of Patent: September 13, 2022Assignee: SAFRAN AIRCRAFT ENGINESInventors: Baptiste Marie Aubin Pierre Jouy, Josselin Luc Florent Sicard, Mathieu Charles Jean Verdiere, Loïc Fabien François Villard
-
Patent number: 11428110Abstract: An abradable structure (36) is provided, with regions (44, 45, 46) with lower resistance to wearing produced by labyrinth seal lips (4, 5), at specific points in the axial direction of the turbomachine, where lip interference could cause the rotor to block up, such as after a temporary shutdown of the turbomachine. These regions may be produced by local weakening (38) or by the abradable material having a structure that is less dense. Application, for example, to turbomachine turbines.Type: GrantFiled: November 20, 2018Date of Patent: August 30, 2022Assignee: SAFRAN AIRCRAFT ENGINESInventors: Baptiste Marie Aubin Pierre Jouy, Mathieu Charles Jean Verdiere
-
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
-
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
-
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
-
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
-
Patent number: 11208909Abstract: A gas turbine engine includes a device for providing sealing between one rotor section and one stator section. The device includes a coating made of an abradable material attached to the stator section. The device further includes a lip on a portion of the rotor section. The lip is configured to form a seal with the abradable material. The gas turbine engine further includes passages for a gaseous fluid and means for blowing such gaseous fluid. The passages open into the rotor section provided with the lip, so that blown gaseous fluid can be present in a zone radially located between the coating and the lip.Type: GrantFiled: June 12, 2018Date of Patent: December 28, 2021Assignee: Safran Aircraft EnginesInventors: Cyrille Telman, Gaël Frédéric Claude Cyrille Evain, Olivier Arnaud Fabien Lambert, Mathieu Charles Jean Verdiere
-
Patent number: 10977149Abstract: A testing environment in which offline simulations can be run to identify policies and/or prediction models that result in more valuable content being included in content pages is described herein. For example, the offline simulations can be run in an application executed by an experiment device using data gathered by a production content delivery system. The simulation application can test any number of different policies and/or prediction models without impacting users that use a production content delivery system to request content.Type: GrantFiled: March 19, 2018Date of Patent: April 13, 2021Assignee: Amazon Technologies, Inc.Inventors: Giovanni Zappella, Cédric Philippe Charles Jean Ghislain Archambeau, Edward Thomas Banti, Michael Brueckner, Borys Marchenko, Martin Milicic, Jurgen Ommen, Dmitrij Scsadej
-
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
-
Patent number: 10942967Abstract: A system uses a trained classifier to identify or predict the item attributes of an item depicted in an image, and compares these attributes to those specified in a corresponding item description. The system may, for example, be used to verify the accuracy of listings submitted by users to an electronic catalog. For example, if an item description submitted by a user does not specify all of the item attributes identified from the item image(s) submitted by the user, the system may generate a suggested edit to the item description.Type: GrantFiled: December 21, 2017Date of Patent: March 9, 2021Assignee: Amazon Technologies, Inc.Inventors: Felix Biessmann, Cédric Philippe Charles Jean Ghislain Archambeau, Charles Shearer Dorner, Karl Anders Gyllstrom, Robert Yuji Haitani, Aengus Gabriel Martin
-
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
-
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
-
Publication number: 20200400033Abstract: An abradable structure (36) is provided, with regions (44, 45, 46) with lower resistance to wearing produced by labyrinth seal lips (4, 5), at specific points in the axial direction of the turbomachine, where lip interference could cause the rotor to block up, such as after a temporary shutdown of the turbomachine. These regions may be produced by local weakening (38) or by the abradable material having a structure that is less dense. Application, for example, to turbomachine turbines.Type: ApplicationFiled: November 20, 2018Publication date: December 24, 2020Inventors: Baptiste Marie Aubin Pierre JOUY, Mathieu Charles Jean VERDIERE