Patents by Inventor Thierry TESSON
Thierry TESSON 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: 10718235Abstract: A turbine ring assembly includes a ring support structure and a plurality of ring sectors made of ceramic matrix composite material, each ring sector having a portion forming an annular base with an inside face defining the inside face of the turbine ring, and an outside face from which there extends a wall defining an internal housing in which a holder member made of metal material is present, the holder member being connected to the ring support structure and including a body from which elastically deformable holder elements extend inside the internal housing on either side of the body, the holder elements bearing against the wall.Type: GrantFiled: March 22, 2016Date of Patent: July 21, 2020Assignee: SAFRAN AIRCRAFT ENGINESInventors: Clément Roussille, Thierry Tesson
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Patent number: 10655501Abstract: A turbine ring assembly includes ring sectors made of ceramic matrix composite material forming a turbine ring and a ring support structure having first and second annular flanges, each ring sector having first and second tabs held between the flanges. First and second holder elements secured to the first annular flange being received in first and second openings in the first tab, while first and second holder elements secured to the second annular flange are in first and second openings in the second tab. Radial clearance is being present when cold between the openings and the portions of the holder elements present in the openings. The first and second annular flanges include, on their faces facing the first and second tabs, a plurality of thrust portions distributed in circumferential manner over the flanges, the ends of the tabs, when cold, being in radial abutment against two thrust portions.Type: GrantFiled: March 20, 2017Date of Patent: May 19, 2020Assignees: SAFRAN CERAMICS, SAFRAN AIRCRAFT ENGINESInventors: Gilles Lepretre, Thierry Tesson, Adéle Lyprendi, Thomas Revel
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Patent number: 10544704Abstract: A turbine ring assembly includes a plurality of ring sectors made of ceramic matrix composite material, together with a ring support structure, each ring sector having a portion forming an annular base with an inner face defining the inner face of the turbine ring and an outer face from which there project at least two tab-forming portions, the ring support structure having at least two attachment tabs extending radially, the tabs of each ring sector gripping the attachment tabs of the ring support structure at least at the radially-inner ends of the attachment tabs.Type: GrantFiled: March 16, 2016Date of Patent: January 28, 2020Assignee: SAFRAN AIRCRAFT ENGINESInventors: Claire Groleau, Gilles Lepretre, Etienne Voland, Thierry Tesson
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Patent number: 10378385Abstract: A turbine ring assembly includes ring sectors made of ceramic matrix composite material forming a turbine ring, and a ring support structure having first and second annular flanges, each ring sector having tabs. The first tab includes an annular groove in which there is received an annular projection of the first flange. The second tab of each ring sector is connected to the ring support structure by a resilient retention element. The second tab includes an opening in which there is received a portion of a retention element secured to the second annular flange of the ring support structure. The retention element is made of a material having a coefficient of thermal expansion that is greater than the coefficient of thermal expansion of the ceramic matrix composite material of the ring sectors.Type: GrantFiled: December 12, 2016Date of Patent: August 13, 2019Assignee: SAFRAN AIRCRAFT ENGINESInventors: Thierry Tesson, Maxime Carlin, Jordan Caron
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Patent number: 10378386Abstract: A turbine ring assembly includes ring sectors forming a turbine ring, and a ring support structure having two annular flanges, each ring sector having a portion forming an annular base with an inner face defining the inside face of the turbine ring and an outer face from which there project at least two tabs, the tabs being retained between the two annular flanges. Each tab of the ring sectors includes a projecting portion on its face situated facing one of the two annular flanges, this projecting portion co-operating with a housing present in the annular flange. Each tab of the ring sectors includes an opening in which there is received a portion of a retention element secured to the annular flange situated facing the tab. The retention element is made of a material having a thermal expansion coefficient that is greater than that of the material of the ring sectors.Type: GrantFiled: December 14, 2016Date of Patent: August 13, 2019Assignee: SAFRAN AIRCRAFT ENGINESInventors: Clément Roussille, Thierry Tesson
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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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Patent number: 10273817Abstract: A turbine ring assembly includes a ring support structure and a plurality of CMC ring sectors forming a turbine ring. Each ring sector is K-shaped in radial section, with tabs extending from the outside face of the annular base over end portions of the annular base, the tabs and the end portions of each ring sector being held respectively facing tabs and end portions of ring sectors that are adjacent in the ring. The turbine ring assembly has a plurality of rigid gaskets, each extending axially between adjacent ring sectors, and resilient holder devices exerting a force suitable for holding the gaskets in contact with the end portions or the tabs of two adjacent ring sectors.Type: GrantFiled: March 31, 2016Date of Patent: April 30, 2019Assignees: SAFRAN CERAMICS, SAFRAN AIRCRAFT ENGINESInventors: Clément Roussille, Thierry Tesson, Freddy Guilbaud
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Publication number: 20190101027Abstract: A turbine ring assembly includes ring sectors made of ceramic matrix composite material forming a turbine ring and a ring support structure having first and second annular flanges, each ring sector having first and second tabs held between the flanges. First and second holder elements secured to the first annular flange being received in first and second openings in the first tab, while first and second holder elements secured to the second annular flange are in first and second openings in the second tab. Radial clearance is being present when cold between the openings and the portions of the holder elements present in the openings. The first and second annular flanges include, on their faces facing the first and second tabs, a plurality of thrust portions distributed in circumferential manner over the flanges, the ends of the tabs, when cold, being in radial abutment against two thrust portions.Type: ApplicationFiled: March 20, 2017Publication date: April 4, 2019Inventors: Gilles LEPRETRE, Thierry TESSON, Adèle LYPRENDI, Thomas REVEL
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Publication number: 20180363506Abstract: A turbine ring assembly includes ring sectors made of ceramic matrix composite material forming a turbine ring, and a ring support structure having first and second annular flanges, each ring sector having tabs. The first tab includes an annular groove in which there is received an annular projection of the first flange. The second tab of each ring sector is connected to the ring support structure by a resilient retention element. The second tab includes an opening in which there is received a portion of a retention element secured to the second annular flange of the ring support structure. The retention element is made of a material having a coefficient of thermal expansion that is greater than the coefficient of thermal expansion of the ceramic matrix composite material of the ring sectors.Type: ApplicationFiled: December 12, 2016Publication date: December 20, 2018Inventors: Thierry TESSON, Maxime CARLIN, Jordan CARON
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Publication number: 20180363507Abstract: A turbine ring assembly includes ring sectors forming a turbine ring, and a ring support structure having two annular flanges, each ring sector having a portion forming an annular base with an inner face defining the inside face of the turbine ring and an outer face from which there project at least two tabs, the tabs being retained between the two annular flanges. Each tab of the ring sectors includes a projecting portion on its face situated facing one of the two annular flanges, this projecting portion co-operating with a housing present in the annular flange. Each tab of the ring sectors includes an opening in which there is received a portion of a retention element secured to the annular flange situated facing the tab. The retention element is made of a material having a thermal expansion coefficient that is greater than that of the material of the ring sectors.Type: ApplicationFiled: December 14, 2016Publication date: December 20, 2018Inventors: Clément ROUSSILLE, Thierry TESSON
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Publication number: 20180080343Abstract: A turbine ring assembly includes a plurality of ring sectors made of ceramic matrix composite material, together with a ring support structure, each ring sector having a portion forming an annular base with an inner face defining the inner face of the turbine ring and an outer face from which there project at least two tab-forming portions, the ring support structure having at least two attachment tabs extending radially, the tabs of each ring sector gripping the attachment tabs of the ring support structure at least at the radially-inner ends of the attachment tabs.Type: ApplicationFiled: March 16, 2016Publication date: March 22, 2018Inventors: Claire GROLEAU, Gilles LEPRETRE, Etienne VOLAND, Thierry TESSON
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Publication number: 20180080344Abstract: A turbine ring assembly includes a ring support structure and a plurality of ring sectors made of ceramic matrix composite material, each ring sector having a portion forming an annular base with an inside face defining the inside face of the turbine ring, and an outside face from which there extends a wall defining an internal housing in which a holder member made of metal material is present, the holder member being connected to the ring support structure and including a body from which elastically deformable holder elements extend inside the internal housing on either side of the body, the holder elements bearing against the wall.Type: ApplicationFiled: March 22, 2016Publication date: March 22, 2018Inventors: Clément ROUSSILLE, Thierry TESSON
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Publication number: 20160290144Abstract: A turbine ring assembly includes a ring support structure and a plurality of CMC ring sectors forming a turbine ring. Each ring sector is K-shaped in radial section, with tabs extending from the outside face of the annular base over end portions of the annular base, the tabs and the end portions of each ring sector being held respectively facing tabs and end portions of ring sectors that are adjacent in the ring. The turbine ring assembly has a plurality of rigid gaskets, each extending axially between adjacent ring sectors, and resilient holder devices exerting a force suitable for holding the gaskets in contact with the end portions or the tabs of two adjacent ring sectors.Type: ApplicationFiled: March 31, 2016Publication date: October 6, 2016Inventors: Clément ROUSSILLE, Thierry TESSON