Patents by Inventor Gael EVAIN
Gael EVAIN 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: 11118477Abstract: A turbine ring assembly includes both a plurality of ring sectors made of ceramic matrix composite material forming a turbine ring, and also a ring support structure. Each ring sector includes a portion forming an annular base with an inner face defining the inside space of the turbine ring and an outer face from which an attachment portion of the ring sector extends for attaching it to the ring support structure. The ring support structure includes two annular flanges between which the attachment portion of each ring sector is held. Each annular flange of the ring support structure presents at least one sloping portion bearing against the attachment portions of the ring sectors, the sloping portion, when observed in meridian section, forming a non-zero angle relative to the radial direction and relative to the axial direction.Type: GrantFiled: May 28, 2020Date of Patent: September 14, 2021Assignee: SAFRAN AIRCRAFT ENGINESInventors: Clement Roussille, Gael Evain, Adele Lyprendi, Lucien Quennehen
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Publication number: 20200291820Abstract: A turbine ring assembly includes both a plurality of ring sectors made of ceramic matrix composite material forming a turbine ring, and also a ring support structure. Each ring sector includes a portion forming an annular base with an inner face defining the inside space of the turbine ring and an outer face from which an attachment portion of the ring sector extends for attaching it to the ring support structure. The ring support structure includes two annular flanges between which the attachment portion of each ring sector is held. Each annular flange of the ring support structure presents at least one sloping portion bearing against the attachment portions of the ring sectors, the sloping portion, when observed in meridian section, forming a non-zero angle relative to the radial direction and relative to the axial direction.Type: ApplicationFiled: May 28, 2020Publication date: September 17, 2020Applicant: SAFRAN AIRCRAFT ENGINESInventors: Clement ROUSSILLE, Gael EVAIN, Adele LYPRENDI, Lucien QUENNEHEN
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Patent number: 10724401Abstract: A turbine ring assembly includes both a plurality of ring sectors made of ceramic matrix composite material forming a turbine ring, and also a ring support structure. Each ring sector includes a portion forming an annular base with an inner face defining the inside space of the turbine ring and an outer face from which an attachment portion of the ring sector extends for attaching it to the ring support structure. The ring support structure includes two annular flanges between which the attachment portion of each ring sector is held. Each annular flange of the ring support structure presents at least one sloping portion bearing against the attachment portions of the ring sectors, the sloping portion, when observed in meridian section, forming a non-zero angle relative to the radial direction and relative to the axial direction.Type: GrantFiled: May 18, 2016Date of Patent: July 28, 2020Assignee: SAFRAN AIRCRAFT ENGINESInventors: Clement Roussille, Gael Evain, Adele Lyprendi, Lucien Quennehen
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Patent number: 10626745Abstract: A turbine ring assembly includes both a plurality of ring sectors made of ceramic matrix composite material forming a turbine ring and also a ring support structure having first and second annular flanges, each ring sector having first and second tabs, the tabs of each ring sector being held between the two annular flanges of the ring support structure. Each of the first and second tabs of the ring sectors has an annular groove. Each of the first and second annular flanges of the ring support structure has an annular projection received respectively in the annular groove of the first tab or in the annular groove of the second tab of each ring sector. A resilient element is interposed between the annular projection of the first flange and the annular grooves of the first tabs, and also between the annular projection of the second flange and the annular grooves of the second tabs.Type: GrantFiled: May 19, 2016Date of Patent: April 21, 2020Assignee: SAFRAN AIRCRAFT ENGINESInventors: Clement Roussille, Gael Evain, Aline Planckeel, Claire Groleau
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Patent number: 10502081Abstract: A turbomachine bearing housing comprising a fixed wall, a rotating shaft, first and second seals between the wall and the shaft, and a chamber between the fixed wall and a stator element supplied with air via an opening close to the shaft. An air guide is arranged along the surface of the wall of the housing, outside same, such that at least a portion of the air exiting the guide passes between the first seal and the shaft, the air guide being supplied with air by an air intake separated radially from the shaft, the air from the air intake being at a higher pressure than at the shaft.Type: GrantFiled: January 15, 2015Date of Patent: December 10, 2019Assignee: SAFRAN AIRCRAFT ENGINESInventors: Jérémy Lucien Jacques Bioud, Sébastien Bourget, Gaël Evain, Eddy Stéphane Joël Fontanel, Florence Irène Noëlle Leutard, Christophe Lima, Giuliana Elisa Rossi
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Patent number: 10329930Abstract: A turbine ring assembly includes a ring support structure and a plurality of ring sectors made of CMC material and forming a turbine ring, each ring sector including an annular base with respective end portions having edges that are held facing an edge of the end portion of the annular base of a sector that is adjacent in the turbine ring. The assembly includes resilient holder devices for holding the ring sectors in position on the ring support structure, and each resilient holder device includes a spring element present beside the outside face of the ring support structure.Type: GrantFiled: March 31, 2016Date of Patent: June 25, 2019Assignees: SAFRAN CERAMICS, SAFRAN AIRCRAFT ENGINESInventors: Clément Roussille, Gael Evain, Aline Planckeel, Claire Groleau, Thierry Tesson
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Publication number: 20180156068Abstract: A turbine ring assembly includes both a plurality of ring sectors made of ceramic matrix composite material forming a turbine ring, and also a ring support structure. Each ring sector includes a portion forming an annular base with an inner face defining the inside space of the turbine ring and an outer face from which an attachment portion of the ring sector extends for attaching it to the ring support structure. The ring support structure includes two annular flanges between which the attachment portion of each ring sector is held. Each annular flange of the ring support structure presents at least one sloping portion bearing against the attachment portions of the ring sectors, the sloping portion, when observed in meridian section, forming a non-zero angle relative to the radial direction and relative to the axial direction.Type: ApplicationFiled: May 18, 2016Publication date: June 7, 2018Applicant: SAFRAN AIRCRAFT ENGINESInventors: Clement ROUSSILLE, Gael EVAIN, Adele LYPRENDI, Lucien QUENNEHEN
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Publication number: 20180149034Abstract: A turbine ring assembly includes both a plurality of ring sectors made of ceramic matrix composite material forming a turbine ring and also a ring support structure having first and second annular flanges, each ring sector having first and second tabs, the tabs of each ring sector being held between the two annular flanges of the ring support structure. Each of the first and second tabs of the ring sectors has an annular groove. Each of the first and second annular flanges of the ring support structure has an annular projection received respectively in the annular groove of the first tab or in the annular groove of the second tab of each ring sector. A resilient element is interposed between the annular projection of the first flange and the annular grooves of the first tabs, and also between the annular projection of the second flange and the annular grooves of the second tabs.Type: ApplicationFiled: May 19, 2016Publication date: May 31, 2018Applicant: SAFRAN AIRCRAFT ENGINESInventors: Clement ROUSSILLE, Gael EVAIN, Aline PLANCKEEL, Claire GROLEAU
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Patent number: 9605547Abstract: A turbine engine wheel, in particular for a low pressure turbine, is provided. The wheel includes blades, each including an airfoil connected by a platform to a middle wall or tang extending radially and itself extended radially inwards by a root mounted in a slot of a disk, the platform and the tang defining two side cavities arranged on either side of the tang, which cavities are circumferentially open and are situated facing corresponding cavities in the directly adjacent blades, and sealing members being housed in the cavities adjacent to the blades. An annular sealing end plate is mounted on the upstream or downstream end of the disk, between the platforms and the disk, so as to face the slots and the roots of the blades, and includes a rotary coupling device for coupling with at least one of the sealing members.Type: GrantFiled: May 30, 2014Date of Patent: March 28, 2017Assignee: SNECMAInventors: Gael Evain, Didier Fabre
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Publication number: 20160341059Abstract: A turbomachine bearing housing comprising a fixed wall, a rotating shaft, first and second seals between the wall and the shaft, and a chamber between the fixed wall and a stator element supplied with air via an opening close to said shaft. An air guide means is arranged along the surface of the wall of the housing, outside same, such that at least a portion of the air exiting the guide means passes between the first seal and the shaft, said guide means being supplied with air by an air intake separated radially from the shaft, the air from the air intake being at a higher pressure than at the shaft.Type: ApplicationFiled: January 15, 2015Publication date: November 24, 2016Applicant: SNECMAInventors: Jérémy Lucien Jacques Bioud, Sébastien Bourget, Gaël Evain, Eddy Stphane Joél Fontanel, Florence Irène Noëlle Leutard, Christophe Lima, Giuliana Elisa Rossi
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Publication number: 20160290145Abstract: A turbine ring assembly includes a ring support structure and a plurality of ring sectors made of CMC material and forming a turbine ring, each ring sector including an annular base with respective end portions having edges that are held facing an edge of the end portion of the annular base of a sector that is adjacent in the turbine ring. The assembly includes resilient holder devices for holding the ring sectors in position on the ring support structure, and each resilient holder device includes a spring element present beside the outside face of the ring support structure.Type: ApplicationFiled: March 31, 2016Publication date: October 6, 2016Inventors: Clément ROUSSILLE, Gael EVAIN, Aline PLANCKEEL, Claire GROLEAU
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Patent number: 9027876Abstract: A device for suspending a turbojet casing, the device including a shouldered pin extending through aligned orifices of two lugs of a clevis secured to the casing. A protection piece for providing protection against wear is mounted on each lug of the clevis and has the shouldered pin passing therethrough, the protection piece being prevented from moving in rotation on the lug by co-operating shapes.Type: GrantFiled: March 21, 2012Date of Patent: May 12, 2015Assignee: SnecmaInventors: Didier Noël Durand, Gaël Evain, Florence Irène Noëlle Leutard, Arnaud Martin
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Publication number: 20150010404Abstract: A turbine or compressor stage suitable for being included in airplane turbojets. According to the invention, the stage comprises a disk (30) configured to be coupled to a shaft of the turbine engine, and at least one airfoil (20), the disk (30) comprising a metal material, the airfoil (20) comprising a ceramic matrix composite material, and the stage further including an interface part (40) that is distinct from the airfoil (20) and that is configured to be fastened to the disk (30) and to fasten said at least one airfoil (20), said interface part (40) comprising a ceramic or a ceramic matrix composite material.Type: ApplicationFiled: July 1, 2014Publication date: January 8, 2015Applicant: SNECMAInventors: Son LE HONG, Gael EVAIN, Didier FABRE, Philippe PICOT
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Publication number: 20140356173Abstract: The invention relates to a turbine engine wheel (2), in particular for a low pressure turbine (1), the wheel having blades (4), each comprising an airfoil (5) connected by a platform (6) to a middle wall or tang (7) extending radially and itself extended radially inwards by a root (8) mounted in a slot of a disk (3), the platform (6) and the tang (7) defining two side cavities (19) arranged on either side of the tang (7), which cavities (19) are circumferentially open and are situated facing corresponding cavities (19) in the directly adjacent blades (4), sealing members (18) being housed in the cavities (19) adjacent to the blades (4). An annular sealing end plate (26) is mounted on the upstream or downstream end of the disk (3), between the platforms (6) and the disk (3), so as to face the slots and the roots (8) of the blades (4), and including rotary coupling means (27) for coupling with at least one of the sealing members (18).Type: ApplicationFiled: May 30, 2014Publication date: December 4, 2014Applicant: SNECMAInventors: Gael EVAIN, Didier FABRE
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Publication number: 20140077027Abstract: A device for suspending a turbojet casing, the device including a shouldered pin extending through aligned orifices of two lugs of a clevis secured to the casing. A protection piece for providing protection against wear is mounted on each lug of the clevis and has the shouldered pin passing therethrough, the protection piece being prevented from moving in rotation on the lug by co-operating shapes.Type: ApplicationFiled: March 21, 2012Publication date: March 20, 2014Applicant: SNECMAInventors: Didier Noël Durand, Gaël Evain, Florence Irène Noëlle Leutard, Arnaud Martin