Patents by Inventor Gilles Lepretre
Gilles Lepretre 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: 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: 10578054Abstract: A variable section nozzle includes an ejection casing and a plurality of internal flaps arranged in a ring downstream from the ejection casing. Each internal flap is connected to the ejection casing by a movable lever pivotally mounted to the downstream end of the ejection casing. Each lever is movable between a first position in which the internal flaps are in a high position and a second position in which the internal flaps are in a folded-down position. The nozzle includes a plurality of rigid movement transmission parts distributed circumferentially around the ejection casing. Each rigid movement transmission part is connected to two adjacent levers by connecting rods, and to a control actuator. Each rigid movement transmission part can move in a direction corresponding to the axial direction of the nozzle under the action of the control actuator to move the adjacent levers between the first and second positions.Type: GrantFiled: May 12, 2017Date of Patent: March 3, 2020Assignees: SAFRAN CERAMICS, SAFRAN AIRCRAFT ENGINESInventors: Gilles Lepretre, Julien Tran
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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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Publication number: 20190226425Abstract: A variable section nozzle includes an ejection casing and a plurality of internal flaps arranged in a ring downstream from the ejection casing. Each internal flap is connected to the ejection casing by a movable lever pivotally mounted to the downstream end of the ejection casing. Each lever is movable between a first position in which the internal flaps are in a high position and a second position in which the internal flaps are in a folded-down position. The nozzle includes a plurality of rigid movement transmission parts distributed circumferentially around the ejection casing. Each rigid movement transmission part is connected to two adjacent levers by connecting rods, and to a control actuator. Each rigid movement transmission part can move in a direction corresponding to the axial direction of the nozzle under the action of the control actuator to move the adjacent levers between the first and second positions.Type: ApplicationFiled: May 12, 2017Publication date: July 25, 2019Applicants: SAFRAN CERAMICS, SAFRAN AIRCRAFT ENGINESInventors: Gilles LEPRETRE, Julien TRAN
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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: 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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Patent number: 7412834Abstract: An annular combustion chamber for a turbomachine comprises inner and outer annular walls united by a transverse wall, the inner and outer walls are extended at their downstream ends by inner and outer fastener flanges for fastening respectively to inner and outer shells of a turbomachine casing in order to hold the combustion chamber in position, the inner flange being provided with a plurality of holes for feeding cooling air to a high pressure turbine of the turbomachine, the air feed holes through the inner flange being distributed circumferentially over at least two rows disposed in a staggered configuration.Type: GrantFiled: April 7, 2005Date of Patent: August 19, 2008Assignee: SNECMAInventors: Martine Bes, Didier Hernandez, Gilles Lepretre, Denis Trahot
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Patent number: 7409831Abstract: A jet engine that provides for the sealing of bleeding air to the cabin, the air passing through a cavity delimited, on the one hand, by the external shell of the compressor and an annular structure connected to the shell, and, on the other hand, by the external casing of the diffuser grating and a strut connected to the external casing and to an external engine casing shell, this external casing shell being fastened to the annular structure by bolting. A tube is provided between the orifice in the strut and the outlet vent, a first end of which tube is mounted in the outlet vent by a connection which is free to rotate and prevented from translational movement, and a second end of which tube is mounted in the orifice by a connection which is free to rotate and free to move translationally.Type: GrantFiled: September 13, 2004Date of Patent: August 12, 2008Assignee: SNECMAInventor: Gilles Lepretre
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Patent number: 7073336Abstract: The invention relates to the sealing of the cavity from which air is bled off to the cabin, which cavity is delimited, on the one hand, by the external shell (6) of the compressor and an annular structure (7) connected to the shell, and, on the other hand, by the external casing (12) of the diffuser grating and a strut (13) connected to said external casing and to an external engine casing shell (14), this external casing shell (14) being fastened to the annular structure (7) by bolting together flanges, using sealing means provided between the annular structure (7) and the external casing (12) of the diffuser grating.Type: GrantFiled: August 30, 2004Date of Patent: July 11, 2006Assignee: Snecma MoteursInventors: Gilles Lepretre, Didier Hernandez
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Patent number: 7040098Abstract: The invention relates to the sealing of the cavity from which air is bled off to the cabin, which cavity is delimited, on the one hand, by the external shell of the compressor and an annular structure connected to the shell, and, on the other hand, by the external casing of the diffuser grating and a strut connected to said external casing and to an external engine casing shell fastened to the annular structure. A first seal is fitted in a first groove provided around the upstream part of the external casing of the diffuser grating, the strips of this first seal bearing on the downstream end of a first projection integral with the annular structure. A second seal is fitted in a second groove provided under said annular structure, the strips of this second seal bearing on the downstream end of a second projection integral with said annular structure and on the end of a third projection formed on the upstream part of the external casing of the diffuser.Type: GrantFiled: August 30, 2004Date of Patent: May 9, 2006Assignee: Snecma MoteursInventors: Gilles Lepretre, Bertrand Monville
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Publication number: 20050229606Abstract: An annular combustion chamber for a turbomachine comprises inner and outer annular walls united by a transverse wall, the inner and outer walls are extended at their downstream ends by inner and outer fastener flanges for fastening respectively to inner and outer shells of a turbomachine casing in order to hold the combustion chamber in position, the inner flange being provided with a plurality of holes for feeding cooling air to a high pressure turbine of the turbomachine, the air feed holes through the inner flange being distributed circumferentially over at least two rows disposed in a staggered configuration.Type: ApplicationFiled: April 7, 2005Publication date: October 20, 2005Applicant: SNECMA MOTEURSInventors: Martine Bes, Didier Hernandez, Gilles Lepretre, Denis Trahot
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Publication number: 20050102994Abstract: The invention relates to the sealing of the cavity for bleeding air to the cabin, which cavity is delimited, on the one hand, by the external shell of the compressor and an annular structure connected to the shell, and, on the other hand, by the external casing of the diffuser grating and a strut connected to said external casing and to an external engine casing shell, this external casing shell being fastened to the annular structure by bolting together flanges, using sealing means provided between the annular structure and the external casing of the diffuser grating, wherein the sealing means consist of a brush seal fastened to the periphery of the upstream part of the external casing of the diffuser grating, said seal having bristles which extend radially outward and bear against the internal surface of a cylindrical sleeve which is integral with the annular structure and surrounds said brush seal.Type: ApplicationFiled: September 13, 2004Publication date: May 19, 2005Applicant: SNECMA MOTEURSInventors: Gilles Lepretre, Laurent Marnas
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Publication number: 20050097899Abstract: The invention relates to the provision of sealing for bleeding air to the cabin, the air passing through a cavity delimited, on the one hand, by the external shell of the compressor and an annular structure connected to the shell, and, on the other hand, by the external casing of the diffuser grating and a strut connected to said external casing and to an external engine casing shell, this external casing shell being fastened to the annular structure by bolting. A tube is provided between the orifice in the strut and the outlet vent, a first end of which tube is mounted in said outlet vent by means of a swivel connection which is free to rotate and prevented from translational movement, and a second end of which tube is mounted in said orifice by means of a swivel connection which is free to rotate and free to move translationally.Type: ApplicationFiled: September 13, 2004Publication date: May 12, 2005Applicant: SNCEMA MOTEURSInventor: Gilles Lepretre
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Publication number: 20050061005Abstract: The invention relates to the sealing of the cavity from which air is bled off to the cabin, which cavity is delimited, on the one hand, by the external shell of the compressor and an annular structure connected to the shell, and, on the other hand, by the external casing of the diffuser grating and a strut connected to said external casing and to an external engine casing shell fastened to the annular structure. A first seal is fitted in a first groove provided around the upstream part of the external casing of the diffuser grating, the strips of this first seal bearing on the downstream end of a first projection integral with the annular structure. A second seal is fitted in a second groove provided under said annular structure, the strips of this second seal bearing on the downstream end of a second projection integral with said annular structure and on the end of a third projection formed on the upstream part of the external casing of the diffuser.Type: ApplicationFiled: August 30, 2004Publication date: March 24, 2005Applicant: SNECOMA MOTEURSInventors: Gilles Lepretre, Bertrand Monville
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Publication number: 20050056025Abstract: The invention relates to the sealing of the cavity from which air is bled off to the cabin, which cavity is delimited, on the one hand, by the external shell (6) of the compressor and an annular structure (7) connected to the shell, and, on the other hand, by the external casing (12) of the diffuser grating and a strut (13) connected to said external casing and to an external engine casing shell (14), this external casing shell (14) being fastened to the annular structure (7) by bolting together flanges, using sealing means provided between the annular structure (7) and the external casing (12) of the diffuser grating.Type: ApplicationFiled: August 30, 2004Publication date: March 17, 2005Applicant: SNECMA MOTEURSInventors: Gilles Lepretre, Didier Hernandez