Patents by Inventor Guillaume Sevi

Guillaume Sevi 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: 11859508
    Abstract: Disclosed is a compressor of a dual-flow aircraft turboshaft engine extending longitudinally along an axis X, the compressor comprising a low-pressure compressor, a high-pressure compressor and an intermediate casing axially connecting the low-pressure compressor and the high-pressure compressor, the high-pressure compressor comprising an inlet guide stator comprising a retaining ring, an outer high-pressure compressor casing and a plurality of vanes, the compressor comprising an immobilising device comprising at least one first member secured to the intermediate casing and at least one second member secured to the retaining ring and configured to cooperate with the first member in order to prevent tangential movement while allowing axial movement and radial movement of the retaining ring relative to the intermediate casing according to the axis X.
    Type: Grant
    Filed: July 10, 2020
    Date of Patent: January 2, 2024
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Thomas Nolwenn Emmanuel Delahaye, Blaise Bergon, Laurent Jablonski, Lilian Yann Dumas, Thomas Etienne Camille Marie Van De Kerckhove, Noël Joseph Camille Robin, Guillaume Sevi
  • Publication number: 20220251975
    Abstract: Disclosed is a compressor of a dual-flow aircraft turboshaft engine extending longitudinally along an axis X, the compressor comprising a low-pressure compressor, a high-pressure compressor and an intermediate casing axially connecting the low-pressure compressor and the high-pressure compressor, the high-pressure compressor comprising an inlet guide stator comprising a retaining ring, an outer high-pressure compressor casing and a plurality of vanes, the compressor comprising an immobilising device comprising at least one first member secured to the intermediate casing and at least one second member secured to the retaining ring and configured to cooperate with the first member in order to prevent tangential movement while allowing axial movement and radial movement of the retaining ring relative to the intermediate casing according to the axis X.
    Type: Application
    Filed: July 10, 2020
    Publication date: August 11, 2022
    Applicant: SAFRAN AIRCRAFT ENGINES
    Inventors: Thomas Nolwenn Emmanuel Delahaye, Blaise Bergon, Laurent Jablonski, Lilian Yann Dumas, Thomas Etienne Camille Marie Van De Kerckhove, Noël Joseph Camille Robin, Guillaume Sevi
  • Patent number: 11261756
    Abstract: 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: Grant
    Filed: May 22, 2017
    Date of Patent: March 1, 2022
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Benoit Argémiro Matthieu Debray, Dominique Michel Fouquet, Grégory Ghosarossian-Prillieux, Guillaume Sevi, Patrick Sultana, Guy Vieillefond
  • Patent number: 11060418
    Abstract: 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: Grant
    Filed: May 15, 2017
    Date of Patent: July 13, 2021
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Benoit Argémiro Matthieu Debray, Dominique Michel Fouquet, Grégory Ghosarossian-Prillieux, Guillaume Sevi, Patrick Sultana, Guy Vieillefond
  • Publication number: 20200325796
    Abstract: 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: Application
    Filed: May 22, 2017
    Publication date: October 15, 2020
    Applicant: SAFRAN AIRCRAFT ENGINES
    Inventors: Benoit Argémiro Matthieu Debray, Dominique Michel Fouquet, Grégory Ghosarossian-Prillieux, Guillaume Sevi, Patrick Sultana, Guy Vieillefond
  • Publication number: 20200326071
    Abstract: 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: Application
    Filed: May 15, 2017
    Publication date: October 15, 2020
    Applicant: SAFRAN AIRCRAFT ENGINES
    Inventors: Benoit Argémiro Matthieu Debray, Dominique Michel Fouquet, Grégory Ghosarossian-Prillieux, Guillaume Sevi, Patrick Sultana, Guy Vieillefond
  • Patent number: 10746056
    Abstract: An exhaust casing of a turbine engine for an aircraft which extends along an axis and includes: a central hub, an annular outer shroud and arms which connect the central hub to the outer shroud, at least one yoke for attaching the exhaust casing to the turbine engine being located on the outer shroud and forming at least one lug extending in a plane perpendicular to the axis and protruding toward the exterior of the outer shroud. The outer shroud includes ribs which form a constant excess of the outer shroud, which are located on either side of the at least one lug of the at least one yoke, and which are aligned with the at least one lug.
    Type: Grant
    Filed: September 20, 2017
    Date of Patent: August 18, 2020
    Assignee: Safran Aircraft Engines
    Inventors: Benoit Argemiro Matthieu Debray, Jeremie Sylvain Bonnaudet, Gregory Ghosarossian-Prillieux, Nicolas Rene Bruno Michelidakis, Guillaume Sevi
  • Patent number: 10677100
    Abstract: A support system (16) for a structural casing of a turbomachine (10), which comprises: a handling fitting (17) comprising a front edge (19) provided with one or more hole(s) (26) for receiving one or more screw(s) (24) for attachment to a flange (23) formed on the casing (10), a rear edge (20) provided with a cavity (32) for receiving a projecting boss (29) formed on the casing (10); a pair of jaws (31) for gripping the boss (29), that are mounted in the cavity (32); at least one screw (33) for adjusting the position of the jaws (31), mounted on the fitting (17) and engaging with at least one jaw (31).
    Type: Grant
    Filed: May 19, 2017
    Date of Patent: June 9, 2020
    Assignee: SAFRAN AIRCRAFT ENGINES
    Inventors: Patrick Sultana, Sébastien Jean Laurent Prestel, Olivier Renon, Benoit Argémiro Matthieu Debray, Guillaume Sevi
  • Publication number: 20190338678
    Abstract: A support system (16) for a structural casing of a turbomachine (10), which comprises: a handling fitting (17) comprising a front edge (19) provided with one or more hole(s) (26) for receiving one or more screw(s) (24) for attachment to a flange (23) formed on the casing (10), a rear edge (20) provided with a cavity (32) for receiving a projecting boss (29) formed on the casing (10); a pair of jaws (31) for gripping the boss (29), that are mounted in the cavity (32); at least one screw (33) for adjusting the position of the jaws (31), mounted on the fitting (17) and engaging with at least one jaw (31).
    Type: Application
    Filed: May 19, 2017
    Publication date: November 7, 2019
    Inventors: Patrick SULTANA, Sébastien Jean Laurent PRESTEL, Olivier RENON, Benoit Argémiro Matthieu DEBRAY, Guillaume SEVI
  • Publication number: 20180080345
    Abstract: The invention relates to an exhaust casing (10) of a turbine engine for an aircraft which extends along an axis and which comprises a central hub (20), an annular outer shroud (30) and arms (40) which connect the central hub (20) to the outer shroud (30), at least one yoke (50) for attaching the exhaust casing (10) to the turbine engine being located on the outer shroud (30) and forming at least one lug (51) extending in a plane perpendicular to the axis and protruding toward the exterior of said outer shroud (30), characterized in that the outer shroud (30) comprises ribs (60) which form a constant excess of said outer shroud (30), which are located on either side of said at least one lug (51) of said at least one yoke (50), and which are aligned with said at least one lug (51).
    Type: Application
    Filed: September 20, 2017
    Publication date: March 22, 2018
    Applicant: Safran Aircraft Engines
    Inventors: Benoit Argemiro Matthieu DEBRAY, Jeremie Sylvain BONNAUDET, Gregory GHOSAROSSIAN-PRILLIEUX, Nicolas Rene Bruno MICHELIDAKIS, Guillaume SEVI
  • Patent number: 9310083
    Abstract: A combustion chamber in which the injection system is attached so as to prevent any axial motion of the injection system, the combustion chamber includes: a baffle including a tubular portion having a first upstream end surrounded by a first radially projecting collar; and an injection system including a bowl which includes a cylindrical portion inserted into the tubular portion, the cylindrical portion including a second upstream end surrounded by a second radially projecting collar, the second collar axially bearing against the first collar, wherein the combustion chamber includes a clamp which axially clamps the first and the second collars against one another, and a fastener which retains the clamp clamped on either side of the first and second collars.
    Type: Grant
    Filed: August 12, 2011
    Date of Patent: April 12, 2016
    Assignee: SNECMA
    Inventors: Jacques Marcel Arthur Bunel, Brice Arnaud Demoulin, Mario César De Sousa, Guillaume Sevi
  • Patent number: 9188064
    Abstract: A fuel injection system for a turbojet engine including a fixed part and a sliding lead-through, the fixed part and the sliding lead-through extending along a reference axis, the fixed part including a cavity that has a bottom and a closure cup, the sliding lead-through being provided with a sole plate contained inside the cavity. The injection system has increased resistance to wearing of the injector on which it is mounted. To achieve this it further includes a spring arranged in such a way as to apply to the sole plate a force capable of preventing the vibration-induced micro-movements of the sliding lead-through with respect to the fixed part in the absence of thermal expansion.
    Type: Grant
    Filed: July 18, 2011
    Date of Patent: November 17, 2015
    Assignee: SNECMA
    Inventors: Jacques Marcel Arthur Bunel, Mario César De Sousa, Guillaume Sevi, Brice Arnaud Demoulin
  • Patent number: 9091445
    Abstract: A turbine engine combustion chamber including at least one ignition sparkplug carried by an outer casing and extending through a guide mechanism carried by a wall forming a body of revolution of the chamber. The guide mechanism includes a tubular guide having the sparkplug passing axially therethrough, which guide is mounted with axial and transverse clearance on a chimney fastened to the wall of the chamber and opening out therein. The guide includes an annular collar engaged with clearance in an internal annular groove of the chimney. The annular collar is urged to press against a wall of the groove by a resilient member mounted in the groove.
    Type: Grant
    Filed: December 3, 2010
    Date of Patent: July 28, 2015
    Assignee: SNECMA
    Inventors: Jacques Marcel Arthur Bunel, Mario Cesar De Sousa, Nicolas Christian Raymond Leblond, Guillaume Sevi, Denis Jean Maurice Sandelis, Christophe Pieussergues
  • Patent number: 9080771
    Abstract: A combustion chamber of a gas turbine engine including a wall, a well secured to the wall, the well forming a recess for a spark plug leading into the combustion chamber, and a spark-plug guide mounted on the well to be transversally mobile relative to the axis of the well, the spark-plug guide including a cylindrical wall portion for guiding and supporting the spark plug and a seal ring mounted such as to engage slidably with a bearing surface of the well. In the combustion chamber the spark-plug guide includes a cooling chamber having openings for supplying cooling air to the chamber.
    Type: Grant
    Filed: November 15, 2010
    Date of Patent: July 14, 2015
    Assignee: SNECMA
    Inventors: Jacques Marcel Arthur Bunel, Mario Cesar De Sousa, Guillaume Sevi
  • Publication number: 20130152603
    Abstract: A combustion chamber in which the injection system is attached so as to prevent any axial motion of the injection system, the combustion chamber includes: a baffle including a tubular portion having a first upstream end surrounded by a first radially projecting collar; and an injection system including a bowl which includes a cylindrical portion inserted into the tubular portion, the cylindrical portion including a second upstream end surrounded by a second radially projecting collar, the second collar axially bearing against the first collar, wherein the combustion chamber includes a clamp which axially clamps the first and the second collars against one another, and a fastener which retains the clamp clamped on either side of the first and second collars.
    Type: Application
    Filed: August 12, 2011
    Publication date: June 20, 2013
    Inventors: Jacques Marcel Arthur Bunel, Brice Arnaud Demoulin, Mario César De Sousa, Guillaume Sevi
  • Publication number: 20130118177
    Abstract: A fuel injection system for a turbojet engine including a fixed part and a sliding lead-through, the fixed part and the sliding lead-through extending along a reference axis, the fixed part including a cavity that has a bottom and a closure cup, the sliding lead-through being provided with a sole plate contained inside the cavity. The injection system has increased resistance to wearing of the injector on which it is mounted. To achieve this it further includes a spring arranged in such a way as to apply to the sole plate a force capable of preventing the vibration-induced micro-movements of the sliding lead-through with respect to the fixed part in the absence of thermal expansion.
    Type: Application
    Filed: July 18, 2011
    Publication date: May 16, 2013
    Applicant: SNECMA
    Inventors: Jacques Marcel Arthur Bunel, Mario César De Sousa, Guillaume Sevi, Brice Arnaud Demoulin
  • Patent number: 8425184
    Abstract: A turbine shroud ring sector for a turbomachine supported at the upstream end by a downstream support of a turbine casing with circular sliding including a first stop able to collaborate with a second stop borne by an element of the turbomachine adjacent to the shroud ring in order to immobilize the shroud ring circularly is disclosed. The sector includes, on an end facing the element, a recess able to allow the second stop to pass to come into contact with the first stop. The recess is cut substantially in the form of a rectangle having, at the bottom of the recess, corners that are rounded in a circular arc of radius r. The bottom of the recess has a convex shape tangential to the circular arcs of the rounded corners and with a curvature that evolves between a radius of curvature r where it meets the rounded corners and a radius of R, greater than the radius r, at a point situated between the two rounded corners.
    Type: Grant
    Filed: January 28, 2010
    Date of Patent: April 23, 2013
    Assignee: Snecma
    Inventors: Bruno Druez, Thomas Langevin, Sebastien Jean Laurent Prestel, Guillaume Sevi
  • Publication number: 20120255275
    Abstract: A turbine engine combustion chamber including at least one ignition sparkplug carried by an outer casing and extending through a guide mechanism carried by a wall forming a body of revolution of the chamber. The guide mechanism includes a tubular guide having the sparkplug passing axially therethrough, which guide is mounted with axial and transverse clearance on a chimney fastened to the wall of the chamber and opening out therein. The guide includes an annular collar engaged with clearance in an internal annular groove of the chimney. The annular collar is urged to press against a wall of the groove by a resilient member mounted in the groove.
    Type: Application
    Filed: December 3, 2010
    Publication date: October 11, 2012
    Applicant: SNECMA
    Inventors: Jacques Marcel Arthur Bunel, Mario Cesar De Sousa, Nicolas Christian Raymond Leblond, Guillaume Sevi, Denis Jean Maurice Sandelis, Christophe Pieussergues
  • Publication number: 20120227373
    Abstract: A combustion chamber of a gas turbine engine including a wall, a well secured to the wall, the well forming a recess for a spark plug leading into the combustion chamber, and a spark-plug guide mounted on the well to be transversally mobile relative to the axis of the well, the spark-plug guide including a cylindrical wall portion for guiding and supporting the spark plug and a seal ring mounted such as to engage slidably with a bearing surface of the well. In the combustion chamber the spark-plug guide includes a cooling chamber having openings for supplying cooling air to the chamber.
    Type: Application
    Filed: November 15, 2010
    Publication date: September 13, 2012
    Applicant: SNECMA
    Inventors: Jacques Marcel Arthur Bunel, Mario Cesar De Sousa, Guillaume Sevi
  • Patent number: 8261556
    Abstract: A device for guiding an element in an orifice in a wall of a turbomachine combustion chamber is disclosed. The device includes a coaxial ring and bushing mounted one inside the other. The bushing includes two coaxial annular parts that are fastened to each other by welding and that define a groove for guiding a rim of the ring. Welding zones between the parts of the bushing are situated away from the path of the rim of the ring when moved along a privileged transverse direction of ring movement relative to the bushing when the combustion chamber is in operation.
    Type: Grant
    Filed: December 4, 2008
    Date of Patent: September 11, 2012
    Assignee: SNECMA
    Inventors: Patrick Audin, Florian Andre Francois Bessagnet, Pierre Pascal Sablayrolles, Guillaume Sevi