Patents by Inventor Guy Vieillefond
Guy Vieillefond 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: 11261756Abstract: A method for manufacturing a casing, for example, an exhaust casing, for a turbomachine. The method generally includes: (a) producing casing sectors, each casing sector having a hub sector, a ferrule sector, and at least one arm linking the hub and ferrule sectors, (b) arranging the casing sectors adjacently and circumferentially, such that each hub sector has longitudinal edges facing longitudinal edges of adjacent hub sectors, (c) welding the longitudinal edges facing the hub sectors, and (d) adding and welding at least a second part of the ferrule to the casing sectors.Type: GrantFiled: May 22, 2017Date of Patent: March 1, 2022Assignee: SAFRAN AIRCRAFT ENGINESInventors: Benoit Argémiro Matthieu Debray, Dominique Michel Fouquet, Grégory Ghosarossian-Prillieux, Guillaume Sevi, Patrick Sultana, Guy Vieillefond
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Patent number: 11060418Abstract: A casing is provided, for example, an exhaust casing for a turbomachine. The casing generally includes an inner hub having an axis of rotation and an outer annular ferrule extending around the hub, the ferrule configured to define, with the hub, an annular flow path for a gas stream. In some examples, the ferrule is rigidly connected to the hub by arms. The hub generally includes, at one longitudinal end, a scalloped annular flange comprising solid portions distributed at regular intervals about said axis and spaced apart from each other by hollow portions. The hub is produced by assembling several angular hub sectors arranged circumferentially end to end around the axis, each hub sector connected to an adjacent hub sector by a longitudinal weld bead that extends over substantially the entire axial extent of the hub and that is substantially aligned axially with a hollow portion of said flange.Type: GrantFiled: May 15, 2017Date of Patent: July 13, 2021Assignee: SAFRAN AIRCRAFT ENGINESInventors: Benoit Argémiro Matthieu Debray, Dominique Michel Fouquet, Grégory Ghosarossian-Prillieux, Guillaume Sevi, Patrick Sultana, Guy Vieillefond
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Publication number: 20200325796Abstract: A method for manufacturing a casing, for example, an exhaust casing, for a turbomachine. The method generally includes: (a) producing casing sectors, each casing sector having a hub sector, a ferrule sector, and at least one arm linking the hub and ferrule sectors, (b) arranging the casing sectors adjacently and circumferentially, such that each hub sector has longitudinal edges facing longitudinal edges of adjacent hub sectors, (c) welding the longitudinal edges facing the hub sectors, and (d) adding and welding at least a second part of the ferrule to the casing sectors.Type: ApplicationFiled: May 22, 2017Publication date: October 15, 2020Applicant: SAFRAN AIRCRAFT ENGINESInventors: Benoit Argémiro Matthieu Debray, Dominique Michel Fouquet, Grégory Ghosarossian-Prillieux, Guillaume Sevi, Patrick Sultana, Guy Vieillefond
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Publication number: 20200326071Abstract: A casing is provided, for example, an exhaust casing for a turbomachine. The casing generally includes an inner hub having an axis of rotation and an outer annular ferrule extending around the hub, the ferrule configured to define, with the hub, an annular flow path for a gas stream. In some examples, the ferrule is rigidly connected to the hub by arms. The hub generally includes, at one longitudinal end, a scalloped annular flange comprising solid portions distributed at regular intervals about said axis and spaced apart from each other by hollow portions. The hub is produced by assembling several angular hub sectors arranged circumferentially end to end around the axis, each hub sector connected to an adjacent hub sector by a longitudinal weld bead that extends over substantially the entire axial extent of the hub and that is substantially aligned axially with a hollow portion of said flange.Type: ApplicationFiled: May 15, 2017Publication date: October 15, 2020Applicant: SAFRAN AIRCRAFT ENGINESInventors: Benoit Argémiro Matthieu Debray, Dominique Michel Fouquet, Grégory Ghosarossian-Prillieux, Guillaume Sevi, Patrick Sultana, Guy Vieillefond
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Patent number: 9291171Abstract: An assembly including a diffuser and an airflow rectifier at an outlet of a centrifugal compressor of a turbine engine, the diffuser being substantially in a shape of a radially positioned double annular disc, and the rectifier being a double toroidal part, arranged as an extension of the double disc of the diffuser and curved such as to divert the airflow in the downstream direction of the engine. The rectifier is attached to the diffuser by a connection positioned immediately adjacent to the contact surface of the two parts and is removable using a standard tool, excluding any other supporting mechanism.Type: GrantFiled: January 19, 2011Date of Patent: March 22, 2016Assignee: SNECMAInventors: Jacques Marcel Arthur Bunel, Sandrine Gandelot, Guy Vieillefond
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Publication number: 20120308374Abstract: An assembly including a diffuser and an airflow rectifier at an outlet of a centrifugal compressor of a turbine engine, the diffuser being substantially in a shape of a radially positioned double annular disc, and the rectifier being a double toroidal part, arranged as an extension of the double disc of the diffuser and curved such as to divert the airflow in the downstream direction of the engine. The rectifier is attached to the diffuser by a connection positioned immediately adjacent to the contact surface of the two parts and is removable using a standard tool, excluding any other supporting mechanism.Type: ApplicationFiled: January 19, 2011Publication date: December 6, 2012Applicant: SNECMAInventors: Jacques Marcel, Arthur Bunel, Sandrine Gandelot, Guy Vieillefond
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Patent number: 8177493Abstract: External shroud for a turbomachine turbine wheel, this shroud being formed of ring sectors (120) positioned circumferentially end to end, and each comprising a circumferentially directed plate (136) bearing a block (138) of abradable material, the plate and the block of each ring sector being offset one with respect to the other in the circumferential direction so that a circumferential end part of the plate of each ring sector overlaps a corresponding end part of the block of an adjacent ring sector.Type: GrantFiled: March 19, 2008Date of Patent: May 15, 2012Assignee: SNECMAInventors: Andre Castel, Bertrand Jean Joseph Marie Heurtel, Sebastien Alain Imbourg, Florence Irene Noelle Leutard, Guy Vieillefond
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Patent number: 7955051Abstract: A diffuser/guide vane assembly for an aircraft turbojet or turboprop engine is disclosed. The diffuser includes annular flanges joined by blades and the guide vane assembly includes cylindrical shelves joined by vanes. The annular flanges and the cylindrical shelves are formed from metal sheets to which the vanes are assembled by brazing.Type: GrantFiled: July 17, 2007Date of Patent: June 7, 2011Assignee: SNECMAInventors: Luc Henri Claude Daguenet, Sandrine Gandelot, Guy Vieillefond
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Publication number: 20100028147Abstract: Diffuser/guide vane assembly (10) for an aircraft turbojet or turboprop engine, the diffuser (12) comprising annular flanges (22, 24) joined by blades (26) and the guide vane assembly (14) comprising cylindrical shelves (28, 30) joined by vanes (32), the annular flanges and the cylindrical shelves being formed from metal sheets to which the vanes (26, 32) are assembled by brazing.Type: ApplicationFiled: July 17, 2007Publication date: February 4, 2010Applicant: SNECMAInventors: Luc Henri Claude DAGUENET, Sandrine GANDELOT, Guy VIEILLEFOND
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Publication number: 20080240915Abstract: External shroud for a turbomachine turbine wheel, this shroud being formed of ring sectors (120) positioned circumferentially end to end, and each comprising a circumferentially directed plate (136) bearing a block (138) of abradable material, the plate and the block of each ring sector being offset one with respect to the other in the circumferential direction so that a circumferential end part of the plate of each ring sector overlaps a corresponding end part of the block of an adjacent ring sector.Type: ApplicationFiled: March 19, 2008Publication date: October 2, 2008Applicant: SNECMAInventors: Andre CASTEL, Bertrand Jean Joseph Marie Heurtel, Sebastien Alain Imbourg, Florence Irene Noelle Leutard, Guy Vieillefond
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Patent number: 7284955Abstract: This present invention concerns an axial gas turbine engine compressor which includes a casing and a distributor wheel composed of a multiplicity of sectors in arcs of circles, with radial stator blades fixed to an external platform, characterized by the fact that the said platform is retained in the casing by two joints of the tongue and groove type, one upstream and the other downstream of the stator blades, the said downstream joint being formed between a transverse flange provided on the external platform and a flange provided on the casing, with a securing resource to create a tight joint between the two flanges. It is preferable that the securing resource should be a bolt. The invention provides for effective retention of the sector so as to prevent wear in the surfaces in contact. The solution is easy to implement.Type: GrantFiled: November 22, 2005Date of Patent: October 23, 2007Assignee: SNECMAInventors: Guy Vieillefond, Christophe Yvon Gabriel Tourne, Bertrand Jean Joseph Marie Heurtel
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Publication number: 20060133939Abstract: This present invention concerns an axial gas turbine engine compressor which includes a casing and a distributor wheel composed of a multiplicity of sectors in arcs of circles, with radial stator blades fixed to an external platform, characterised by the fact that the said platform is retained in the casing by two joints of the tongue and groove type, one upstream and the other downstream of the stator blades, the said downstream joint being formed between a transverse flange provided on the external platform and a flange provided on the casing, with a securing resource to create a tight joint between the two flanges. It is preferable that the securing resource should be a bolt. The invention provides for effective retention of the sector so as to prevent wear in the surfaces in contact. The solution is easy to implement.Type: ApplicationFiled: November 22, 2005Publication date: June 22, 2006Applicant: SNECMAInventors: Guy Vieillefond, Christophe Tourne, Bertrand Heurtel
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Patent number: 6543818Abstract: The present invention relates to an axisymmetric structural component, one of the ends of which is fitted with an inner circular flange for assembling, by bolting. The axisymmetric structural component with a second axisymmetric structural component. The flange comprises housings for receiving fixing elements such as bolts, pins or threaded rods. The housings are arranged on the circumference of the said flange at regular intervals. Each housing is, in longitudinal section (A—A) along a plane passing through the rotational axis of the component, T-shaped and consists of a first essentially cylindrical portion which is longitudinally open on the inner face (x) of the axisymmetric structural component and transversely open on the contact face (y) of the flange in the assembly. A second essentially semi-cylindrical portion is mounted on the flange which is also longitudinally open on the inner face (x) of the said structural component having an essentially D-shaped transverse section.Type: GrantFiled: May 30, 2001Date of Patent: April 8, 2003Assignees: Techspace Aero S.A., Snecma MoteursInventors: Frédéric Leman, Guy Vieillefond, Mathieu Bos, Sébastien Ryhon