Patents by Inventor Thierry Jean-Jacques Obrecht
Thierry Jean-Jacques Obrecht 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: 11767794Abstract: A twin-flow, double body turbojet includes a fan that is positioned upstream from a gas generator and delimits primary and secondary flows. The gas generator is traversed by the primary flow and includes a low-pressure compressor, a high-pressure compressor, a combustion chamber, a high-pressure turbine and a low-pressure turbine. The low-pressure turbine is linked to the low-pressure compressor by a low-pressure rotating shaft, and the high-pressure turbine is linked to the high-pressure compressor by a high-pressure rotating shaft. The turbojet has an electric motor for injecting mechanical power into at least one of the rotating shafts. The turbojet also has a device for removing power from at least one of the rotating shafts and transforming the excess power into electrical energy. An electric storage means is positioned between the device for removing power and the electric motor.Type: GrantFiled: August 4, 2015Date of Patent: September 26, 2023Assignee: SAFRAN AIRCRAFT ENGINESInventors: Bernard Robic, Thierry Jean-Jacques Obrecht, Baptiste Jean Marie Renault
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Patent number: 10024336Abstract: A compressor for a turbine engine, including: a casing, at least one compressor stage including an impeller having stationary blades and an impeller having moving blades positioned downstream of the stationary blade impeller, and cavities in a thickness of the casing that are disposed along a circumference of the casing opposite the moving blades. The cavities, which are elongate and extend along a main direction of orientation, are closed upstream and downstream by upstream and downstream faces respectively, and an upstream border and a downstream border are formed at the intersections between same and the casing. The cavities are offset in relation to the moving blades to overlap the moving blade impeller in the upstream portion, thereby covering the upstream end thereof. The downstream border of the cavities is oriented parallel to the chord at the head of the moving blade.Type: GrantFiled: April 15, 2013Date of Patent: July 17, 2018Assignee: SNECMAInventors: Thierry Jean-Jacques Obrecht, Celine Ghilardi, Vincent Perrot
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Publication number: 20170226934Abstract: twin-flow, double body turbojet includes a fan that is positioned upstream from a gas generator and delimits primary and secondary flows. The gas generator is traversed by the primary flow and includes a low-pressure compressor, a high-pressure compressor, a combustion chamber, a high-pressure turbine and a low-pressure turbine. The low-pressure turbine is linked to the low-pressure compressor by a low-pressure rotating shaft, and the high-pressure turbine is linked to the high-pressure compressor by a high-pressure rotating shaft. The turbojet has an electric motor for injecting mechanical power into at least one of the rotating shafts. The turbojet also has a device for removing power from at least one of the rotating shafts and transforming the excess power into electrical energy. An electric storage means is positioned between the device for removing power and the electric motor.Type: ApplicationFiled: August 4, 2015Publication date: August 10, 2017Applicant: SAFRAN AIRCRAFT ENGINESInventors: Bernard Robic, Thierry Jean-Jacques Obrecht, Baptiste Jean Marie Renault
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Patent number: 9638213Abstract: A casing for a turbine engine compressor, including: cavities in a thickness of the casing, extending in parallel to one another from an inner face of the casing along a circumference thereof, the cavities not being in communication with one another. The cavities, which are elongate and extend along a main direction of orientation between two side walls, are closed upstream and downstream by upstream and downstream faces respectively, and an upstream border and a downstream border are formed at the intersections between same and the inner face of the casing. The upstream border of the cavities takes a form of a wavy line including at least two alternate undulations over a length thereof between the side walls.Type: GrantFiled: April 15, 2013Date of Patent: May 2, 2017Assignee: SNECMAInventors: Thierry Jean-Jacques Obrecht, Olivier Stephane Domercq
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Patent number: 9200638Abstract: A rotor of a turbomachine compressor, including a bladed rotor disk fitted at its radially external end with a wall forming the inner end of an annual flow channel of a primary gas flow, and formed from multiple angular sectors, each of which is delimited between two blades of the disk which are consecutive in a circumferential direction and includes a bulging portion which is convex in the axial direction and in the circumferential direction, together with, upstream from the bulging portion, a troughed portion which is concave in the axial direction and in the circumferential direction and which has a base which is roughly punctiform.Type: GrantFiled: October 1, 2010Date of Patent: December 1, 2015Assignees: SNECMA, CENAEROInventors: Eric Jacques Boston, Alexandre Franck Arnaud Chartoire, Vasiliki Iliopoulou, Ingrid Lepot, Thierry Jean-Jacques Obrecht
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Publication number: 20150078890Abstract: A compressor for a turbine engine, including: a casing, at least one compressor stage including an impeller having stationary blades and an impeller having moving blades positioned downstream of the stationary blade impeller, and cavities in a thickness of the casing that are disposed along a circumference of the casing opposite the moving blades. The cavities, which are elongate and extend along a main direction of orientation, are closed upstream and downstream by upstream and downstream faces respectively, and an upstream border and a downstream border are formed at the intersections between same and the casing. The cavities are offset in relation to the moving blades to overlap the moving blade impeller in the upstream portion, thereby covering the upstream end thereof. The downstream border of the cavities is oriented parallel to the chord at the head of the moving blade.Type: ApplicationFiled: April 15, 2013Publication date: March 19, 2015Applicant: SNECMAInventors: Thierry Jean-Jacques Obrecht, Celine Ghilardi, Vincent Perrot
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Publication number: 20150078889Abstract: A casing for a turbine engine compressor, including: cavities in a thickness of the casing, extending in parallel to one another from an inner face of the casing along a circumference thereof, the cavities not being in communication with one another. The cavities, which are elongate and extend along a main direction of orientation between two side walls, are closed upstream and downstream by upstream and downstream faces respectively, and an upstream border and a downstream border are formed at the intersections between same and the inner face of the casing. The upstream border of the cavities takes a form of a wavy line including at least two alternate undulations over a length thereof between the side walls.Type: ApplicationFiled: April 15, 2013Publication date: March 19, 2015Applicant: SNECMAInventors: Thierry Jean-Jacques Obrecht, Olivier Stephane Domercq
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Publication number: 20120201692Abstract: A rotor of a turbomachine compressor, including a bladed rotor disk fitted at its radially external end with a wall forming the inner end of an annual flow channel of a primary gas flow, and formed from multiple angular sectors, each of which is delimited between two blades of the disk which are consecutive in a circumferential direction and includes a bulging portion which is convex in the axial direction and in the circumferential direction, together with, upstream from the bulging portion, a troughed portion which is concave in the axial direction and in the circumferential direction and which has a base which is roughly punctiform.Type: ApplicationFiled: October 1, 2010Publication date: August 9, 2012Applicants: CENAERO, SNECMAInventors: Eric Jacques Boston, Alexandre Franck Arnaud Chartoire, Vasiliki Iliopoulou, Ingrid Lepot, Thierry Jean-Jacques Obrecht
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Patent number: 8182209Abstract: Reinjecting air to the inlet of a compressor in order to improve its pumping margin. The inlet stator of the compressor includes injection holes passing through at least some of the vanes in the vicinity of their pivots.Type: GrantFiled: May 29, 2008Date of Patent: May 22, 2012Assignee: SNECMAInventors: Michel Gilbert Roland Brault, Thierry Jean-Jacques Obrecht
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Patent number: 7845901Abstract: Devices for intaking gases from the boundary layer through ducts hollowed out in blades. These devices are suitable for variable setting blades, installed on the stator using pivots. The seal is maintained despite the variation in the relative position between the moving pivots through which ducts pass, and the fixed intake header pipe.Type: GrantFiled: January 12, 2006Date of Patent: December 7, 2010Assignee: SNECMAInventors: Stephan Yves Aubin, Thomas Julien Roland Earith, Didier Rene Andre Escure, Thierry Jean-Jacques Obrecht, Stephane Rousselin
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Publication number: 20080298951Abstract: Reinjecting air to the inlet of a compressor in order to improve its pumping margin. The inlet stator of the compressor includes injection holes passing through at least some of the vanes in the vicinity of their pivots.Type: ApplicationFiled: May 29, 2008Publication date: December 4, 2008Applicant: SNECMAInventors: Michel Gilbert Roland Brault, Thierry Jean-Jacques Obrecht