Patents by Inventor Sebastien Jean-Laurent Prestel
Sebastien Jean-Laurent Prestel 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: 9957896Abstract: A device for axially arresting a sealing ring made of an abradable material in contact with a periphery of an aircraft turbomachine module rotor, the device having a first reference central axis, and including: a support including a support opening defining a circular track centered on a second axis at a distance from the axis; and an axial stop part including an extraction passage centered on a third axis at a distance from the axis, and defining a complementary circular track around its periphery, cooperating with the track to allow the part to rotate about the axis, between an axial stop position for the sealing ring, and a position to extract the ring through the extraction passage.Type: GrantFiled: December 4, 2012Date of Patent: May 1, 2018Assignee: SNECMAInventors: Olivier Belmonte, Sebastien Jean Laurent Prestel
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Publication number: 20170218785Abstract: A turbomachine module, comprising a mobile wheel rotatably mounted inside a housing of the module and surrounded by a sectorised sealing ring (18) that comprises an annular row of sectors, each ring sector comprising at least one circumferential hook that is configured to engage with an annular hooking rail of the housing, the module further comprising a sectorised protective annular shim (50) that is interposed between the hooks of the ring sectors and the rail of the housing and that comprises an annular row of sectors of shim, characterised in that the edges (60) of the circumferential ends of the sectors of shim are not aligned with the edges (58) of the circumferential ends of the ring sectors along the longitudinal axis of the module.Type: ApplicationFiled: August 4, 2015Publication date: August 3, 2017Inventors: Cyril LOISEAU, Alain Dominique GENDRAUD, Sebastien Jean Laurent PRESTEL
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Patent number: 9683452Abstract: A turbine for a gas turbine engine comprising at least one turbine stator and one turbine rotor, said turbine stator comprising at least one inner annular platform, said inner platform comprising a radial wall delimiting at least one cavity between the turbine stator and the turbine rotor, wherein the turbine rotor comprises at least one elongate element positioned substantially axially and defining a sealing baffle in said cavity, and in that the turbine stator comprises at least one element made of abradable material designed to engage with said elongate element of the turbine rotor so as to form a labyrinth seal.Type: GrantFiled: December 19, 2013Date of Patent: June 20, 2017Assignee: SNECMAInventors: Florent Pierre Antoine Luneau, Alain Dominique Gendraud, Patrick Joseph Marie Girard, Sebastien Jean Laurent Prestel
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Patent number: 9631557Abstract: A sealing device for a nozzle of a turbomachine turbine including a turbine rotor. The turbine nozzle includes at least one inner annular platform. The turbine rotor includes a downstream spoiler disposed substantially axially. The sealing device includes at least one sealing sheet disposed, radially, between the inner face of the inner platform and the downstream spoiler of the rotor of the turbine so as to form an overlap clearance.Type: GrantFiled: May 4, 2012Date of Patent: April 25, 2017Assignee: SNECMAInventors: Florent Pierre Antoine Luneau, Patrick Joseph Marie Girard, Sebastien Jean Laurent Prestel, Jean-Luc Soupizon
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Publication number: 20150377047Abstract: A nozzle sector of an aircraft turbo-machine, including a hooking member (64) having a projection (70, 70a, 70b) radially extending towards the outside of the sector, a recess (72) being provided through at least one part of a distal end of the projection (70, 70a, 70b), the recess (72) being configured to accommodate a shoulder member (74) forming a stop for a surface of an adjacent sector (26).Type: ApplicationFiled: February 19, 2014Publication date: December 31, 2015Inventors: Sébastien Jean Laurent Prestel, Denis Aydin, Rémi Blanc, Hélène Condat, Patrice Jean-Marc Rosset
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Publication number: 20150345328Abstract: A holding device of a cooling tube for a turbojet casing, the holding device including a first plate configured to be arranged in integral contact with a turbojet casing; a second plate, the first and second plates having a gap therebetween; a first spacer and the second spacer which are arranged between the first plate and the second plate and defining the gap between the first and second plates, the first and second spacers having a spacing therebetween suitable for passing the cooling tube.Type: ApplicationFiled: May 26, 2015Publication date: December 3, 2015Inventor: Sébastien Jean Laurent PRESTEL
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Publication number: 20150118035Abstract: A turbine stage for a turbine engine, the stage including a nozzle and a wheel mounted inside a sectorized ring carried by a casing. The nozzle is attached to the casing and is retained axially downstream by bearing against an annular split ring. Each ring sector includes at its upstream end a member of C-shaped section that is engaged on the casing rail and that holds the split ring radially. A radially inner wall of the C-shaped member of each ring sector extends inside the split ring over an entire axial dimension thereof and its upstream end portion is engaged in at least one recess of the nozzle.Type: ApplicationFiled: April 17, 2013Publication date: April 30, 2015Applicant: SNECMAInventors: Alain Dominique Gendraud, Alberto Martin-Matos, Vincent Millier, Sebastien Jean Laurent Prestel
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Patent number: 8961117Abstract: A turbine stage of a turbine engine, the stage including a rotor wheel mounted inside a sectorized ring carried by an outer casing, the outer casing including at least a circumferential rim housed in an annular cavity to attach a downstream end of the ring sector. A bottom wall of the annular cavity of the ring sector remains radially spaced apart from the circumferential rim of the outer casing to provide a thermally insulating space between them and includes a radial positioning mechanism acting on the circumferential rim.Type: GrantFiled: November 24, 2010Date of Patent: February 24, 2015Assignee: SnecmaInventors: Fabrice Marcel Noel Garin, Alain Dominique Gendraud, Gilles Jeannin, Sebastien Jean Laurent Prestel
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Publication number: 20140341722Abstract: A device for axially arresting a sealing ring made of an abradable material in contact with a periphery of an aircraft turbomachine module rotor, the device having a first reference central axis, and including: a support including a support opening defining a circular track centered on a second axis at a distance from the axis; and an axial stop part including an extraction passage centered on a third axis at a distance from the axis, and defining a complementary circular track around its periphery, cooperating with the track to allow the part to rotate about the axis, between an axial stop position for the sealing ring, and a position to extract the ring through the extraction passage.Type: ApplicationFiled: December 4, 2012Publication date: November 20, 2014Applicant: SNECMAInventors: Olivier Belmonte, Sebastien Jean Laurent Prestel
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Publication number: 20140205442Abstract: A sealing device for a nozzle of a turbomachine turbine including a turbine rotor. The turbine nozzle includes at least one inner annular platform. The turbine rotor includes a downstream spoiler disposed substantially axially. The sealing device includes at least one sealing sheet disposed, radially, between the inner face of the inner platform and the downstream spoiler of the rotor of the turbine so as to form an overlap clearance.Type: ApplicationFiled: May 4, 2012Publication date: July 24, 2014Applicant: SNECMAInventors: Florent Pierre Antoine Luneau, Patrick Joseph, Marie Girard, Sebastien Jean-Laurent Prestel, Jean-Luc Soupizon
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Patent number: 8734100Abstract: A turbine stage for a turbomachine, the stage comprising a rotor wheel mounted inside a sectorized ring carried by an outer casing, and a sectorized nozzle fastened to the casing downstream from the wheel, each ring sector having a downstream end that is held bearing radially outwards against a cylindrical rail of the casing by means of the nozzle, the casing rail including an annular row of through radial notches reducing the areas for heat exchange by conduction both between the casing and the ring sectors and between the casing and the nozzle.Type: GrantFiled: June 27, 2011Date of Patent: May 27, 2014Assignee: SNECMAInventors: Fabrice Marcel Noel Garin, Alain Dominique Gendraud, Thierry Lequitte, Sebastien Jean Laurent Prestel
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Publication number: 20140105732Abstract: A turbine for a gas turbine engine comprising at least one turbine stator and one turbine rotor, said turbine stator comprising at least one inner annular platform, said inner platform comprising a radial wall delimiting at least one cavity between the turbine stator and the turbine rotor, wherein the turbine rotor comprises at least one elongate element positioned substantially axially and defining a sealing baffle in said cavity, and in that the turbine stator comprises at least one element made of abradable material designed to engage with said elongate element of the turbine rotor so as to form a labyrinth seal.Type: ApplicationFiled: December 19, 2013Publication date: April 17, 2014Applicant: SNECMAInventors: Florent Pierre Antoine LUNEAU, Alain Dominique Gendraud, Patrick Joseph Marie Girard, Sebastien Jean Laurent Prestel
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Patent number: 8425184Abstract: 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: GrantFiled: January 28, 2010Date of Patent: April 23, 2013Assignee: SnecmaInventors: Bruno Druez, Thomas Langevin, Sebastien Jean Laurent Prestel, Guillaume Sevi
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Publication number: 20120288362Abstract: A turbine stage of a turbine engine, the stage including a rotor wheel mounted inside a sectorized ring carried by an outer casing, the outer casing including at least a circumferential rim housed in an annular cavity to attach a downstream end of the ring sector. A bottom wall of the annular cavity of the ring sector remains radially spaced apart from the circumferential rim of the outer casing to provide a thermally insulating space between them and includes a radial positioning mechanism acting on the circumferential rim.Type: ApplicationFiled: November 24, 2010Publication date: November 15, 2012Applicant: SNECMAInventors: Fabrice Marcel Noel Garin, Alain Dominique Gendraud, Gilles Jeannin, Sebastien Jean Laurent Prestel
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Patent number: 8303246Abstract: Assembly of the connection of an arm to a ferrule is done by imbricating a side wing protruding from the end of the arm and keys bolted to the ferrule. The assembly may be supplemented with positioning pins.Type: GrantFiled: October 14, 2008Date of Patent: November 6, 2012Assignee: SnecmaInventors: Godefroy Francis Frederic Drelon, Sebastien Jean Laurent Prestel, Jean-Luc Soupizon
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Patent number: 8221061Abstract: The present invention relates to a two-spool gas turbine engine including an HP turbine stator ring and an exterior wall of the transition channel between the HP and LP stages, a first enclosure for controlling the stator ring, and a second enclosure for distributing air for blowing the exterior wall of the transition channel. The engine is characterized in that the two enclosures are placed in communication via an orifice controlled by a valve adapted to be open when the pressure P1 in the first enclosure is greater than the pressure P2 in the second enclosure, and closed when P1<P2.Type: GrantFiled: January 9, 2009Date of Patent: July 17, 2012Assignee: SNECMAInventors: Aurelien Rene-Pierre Massot, Philippe Jean-Pierre Pabion, Sebastien Jean Laurent Prestel, Jean-Luc Soupizon
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Patent number: 8172526Abstract: The exhaust casing of a turbomachine includes a cylindrical jacket for guiding a flow of exhaust gas and for defining a hub cavity inside the casing, the jacket including at its ends an annular flange and a radial annular portion extending inwards and formed with an annular rim that is designed to be received in an annular groove of the inner wall of the exhaust casing to close the hub cavity in substantially sealed manner.Type: GrantFiled: December 9, 2008Date of Patent: May 8, 2012Assignee: SNECMAInventors: Xavier Firmin Camille Jean Lescure, Aurelien Rene-Pierre Massot, Sebastien Jean Laurent Prestel, Christian Rene Schnell
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Patent number: 8162593Abstract: An inter-turbine casing for a turbofan is disclosed. The casing includes an outer ring, an inner ring, and an intermediate ring between the inner ring and the outer ring. The inner and intermediate rings have respective openings for the passage of cooling air. The casing includes at least one sealing device, arranged between the outer ring and the intermediate ring, with a base, provided with at least one orifice for the passage of cooling air, and a peripheral skirt which is able to be compressed and expanded elastically. The base bears against the outer ring and the peripheral skirt bears against the intermediate ring.Type: GrantFiled: March 19, 2008Date of Patent: April 24, 2012Assignee: SNECMAInventors: Jean-Michel Bernard Guimbard, Philippe Jean-Pierre Pabion, Sebastien Jean Laurent Prestel, Jean-Luc Soupizon
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Patent number: 8147189Abstract: A sectorized nozzle for a turbomachine, the nozzle being made up of cylindrical sectors and comprising two annular platforms interconnected by substantially radial vanes, together with an annular rail for supporting elements of abradable material, each inner platform having longitudinally-extending edges that are V-shaped, and each rail sector having, on at least one of its sides, means for bearing axially on corresponding means provided on an adjacent nozzle sector.Type: GrantFiled: December 9, 2008Date of Patent: April 3, 2012Assignee: SNECMAInventors: Patrick Joseph Marie Girard, Xavier Firmin Camille Jean Lescure, Aurelien Rene-Pierre Massot, Sebastien Jean Laurent Prestel
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Patent number: 8142152Abstract: The connection assembly of an arm to a sleeve is carried out substantially by parts of axes crossing the arm and the spacers between the parts of axes and the sleeve and the assembly bolts. The assembly and the disassembly are easy, even with highly reduced encumbrance, as the connection is light and devoid of high internal efforts, and a good position precision is obtained. The assembly may be applied to stators with an exterior sleeve and, an interior hub and radial link arms, which are encountered in certain turbomachines.Type: GrantFiled: October 28, 2008Date of Patent: March 27, 2012Assignee: SNECMAInventors: Godefroy Francis Frederic Drelon, Sebastien Jean Laurent Prestel, Jean-Luc Soupizon