Patents by Inventor Olivier Stephane Domercq
Olivier Stephane Domercq 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: 9759234Abstract: A turbine engine has at least two successive annular rows of stationary vanes, e.g. formed by the vanes of a nozzle and by an annular row of casing arms arranged downstream from the nozzle Each casing arm extends substantially in a radial plane passing between the trailing edges of two adjacent stationary vanes of the nozzle, and the pitch between these two stationary vanes is greater than the pitch between the other stationary vanes of the nozzle, in such a manner that the wakes formed at the trailing edges of these two stationary vanes pass respectively on either side of the corresponding casing arm.Type: GrantFiled: June 17, 2011Date of Patent: September 12, 2017Assignee: SNECMAInventors: Olivier Stephane Domercq, Vincent Paul Gabriel Perrot, Hanna Reiss, Jean-Francois Rios
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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: 9334878Abstract: A blade assembly for a turbomachine compressor includes a plurality of individual devices acting on the flow. The individual devices are provided upstream of the blade assembly and are formed at least so as to generate vortices. Each of the individual devices is arranged on an upstream face of a shroud around which a recirculating flow passes, circulating in a cavity. The recirculating flow is reinjected into the principal flow such that the individual devices act simultaneously on the principal flow and on the recirculating flow.Type: GrantFiled: May 25, 2011Date of Patent: May 10, 2016Assignee: SNECMAInventors: Olivier Stephane Domercq, Vincent Paul Gabriel Perrot, Agnes Pesteil
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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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Patent number: 8974175Abstract: A turbomachine compressor including variable-pitch vanes including an aerofoil section connected by a mounting plate of circular outline to a pivot guided in rotation in an orifice in a casing is disclosed. The mounting plate of the vane includes at least one notch for bleeding air from the compressor stream. The notch is intended to communicate with a hole in the casing in order to remove the air bled off when the vanes are in a first position, and to be closed off by this casing when the vanes are in a second position, so that the flow rate of bled air depends on the pitch angle of the vanes.Type: GrantFiled: June 15, 2009Date of Patent: March 10, 2015Assignee: SNECMAInventors: Olivier Stephane Domercq, Vincent Paul Gabriel Perrot
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Patent number: 8777558Abstract: A casing for a turbomachine rotor wheel includes a plurality of circumferential grooves, each of substantially constant section, with the section areas of the circumferential grooves decreasing from upstream to downstream on going from the first groove to the last groove. By treating the casing in this way, the efficiency of the rotor wheel is optimized and its surge margin is improved.Type: GrantFiled: March 25, 2009Date of Patent: July 15, 2014Assignee: SNECMAInventors: Antoine Robert Alain Brunet, Olivier Stephane Domercq, Laurent Jablonski, Vincent Paul Gabriel Perrot
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Patent number: 8491254Abstract: A turbomachine compressor including variable-pitch vanes, each including an airfoil connected via a plate of circular outline to a pivot guided to pivot in an orifice in a casing, the plate including an air feed duct including one end for communication with a passage formed in the casing when the vane is in a first position, so as to inject air into the annulus of the compressor upstream from the vane, and to be closed by the casing when the vane is in a second position.Type: GrantFiled: April 15, 2009Date of Patent: July 23, 2013Assignee: SNECMAInventors: Olivier Stephane Domercq, Vincent Paul Gabriel Perrot, Jean-Pierre Poitevin
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Publication number: 20130064673Abstract: A blade assembly for a turbomachine compressor includes a plurality of individual devices acting on the flow. The individual devices are provided upstream of the blade assembly and are formed at least so as to generate vortices. Each of the individual devices is arranged on an upstream face of a shroud around which a recirculating flow passes, circulating in a cavity. The recirculating flow is reinjected into the principal flow such that the individual devices act simultaneously on the principal flow and on the recirculating flow.Type: ApplicationFiled: May 25, 2011Publication date: March 14, 2013Applicant: SNECMAInventors: Olivier Stephane Domercq, Vincent Paul Gabriel Perrot, Agnes Pesteil
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Publication number: 20130058776Abstract: A turbine engine has at least two successive annular rows of stationary vanes, e.g. formed by the vanes of a nozzle and by an annular row of casing arms arranged downstream from the nozzle Each casing arm extends substantially in a radial plane passing between the trailing edges of two adjacent stationary vanes of the nozzle, and the pitch between these two stationary vanes is greater than the pitch between the other stationary vanes of the nozzle, in such a manner that the wakes formed at the trailing edges of these two stationary vanes pass respectively on either side of the corresponding casing arm.Type: ApplicationFiled: June 17, 2011Publication date: March 7, 2013Applicant: SNECMAInventors: Olivier Stephane Domercq, Vincent Paul Gabriel Perrot, Hanna Reiss, Jean-Francois Rios
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Publication number: 20110110773Abstract: Turbomachine compressor comprising variable-pitch vanes comprising an aerofoil section connected by a mounting plate (17) of circular outline to a pivot (18) guided in rotation in an orifice in a casing (14), the mounting plate of the vane comprising at least one notch (60) for bleeding air from the compressor stream, this notch being intended to communicate with a hole (62) in the casing in order to remove the air bled off when the vanes are in a first position, and to be closed off by this casing when the vanes are in a second position, so that the flow rate of bled air depends on the pitch angle of the vanes.Type: ApplicationFiled: June 15, 2009Publication date: May 12, 2011Applicant: SNECMAInventors: Olivier Stephane Domercq, Vincent Paul Gabriel Perrot
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Publication number: 20110085896Abstract: A casing for a turbomachine rotor wheel includes a plurality of circumferential grooves, each of substantially constant section, with the section areas of the circumferential grooves decreasing from upstream to downstream on going from the first groove to the last groove. By treating the casing in this way, the efficiency of the rotor wheel is optimized and its surge margin is improved.Type: ApplicationFiled: March 25, 2009Publication date: April 14, 2011Applicant: SNECMAInventors: Antoine Robert Alain Brunet, Olivier Stephane Domercq, Laurent Jablonski, Vincent Paul Gabriel Perrot
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Publication number: 20110058931Abstract: A turbomachine compressor including variable-pitch vanes, each including an airfoil connected via a plate of circular outline to a pivot guided to pivot in an orifice in a casing, the plate including an air feed duct including one end for communication with a passage formed in the casing when the vane is in a first position, so as to inject air into the annulus of the compressor upstream from the vane, and to be closed by the casing when the vane is in a second position.Type: ApplicationFiled: April 15, 2009Publication date: March 10, 2011Applicant: SNECMAInventors: Olivier Stephane Domercq, Vincent Paul Gabriel Perrot, Jean-Pierre Poitevin