Patents by Inventor Christophe Simonet
Christophe Simonet 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: 11008869Abstract: The present application provides a rotor for use in a turbine engine. The rotor may include a first rotor disc, a second rotor disc adjacent to the first rotor disc, and a belly band seal positioned between the first rotor disc and the second rotor disc. The belly band seal may include a band seal with a locking tab brazed thereon.Type: GrantFiled: April 25, 2018Date of Patent: May 18, 2021Assignee: General Electric Technology GmbHInventors: Christophe Simonet, Marco Christof Pawlowski, Giovanni Cataldi
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Patent number: 10415395Abstract: A method is disclosed for cooling a gas turbine having a turbine, wherein a rotor, which rotates about a machine axis, carries a plurality of rotating blades, which are mounted by blade roots and extend with their airfoils into a hot gas path of the gas turbine. The rotor is concentrically surrounded by a turbine vane carrier carrying a plurality of stationary vanes, whereby the rotating blades and the stationary vanes are arranged in alternating rows in axial direction. An extended lifetime with external cooling is achieved by providing first and second cooling systems for the turbine.Type: GrantFiled: May 13, 2016Date of Patent: September 17, 2019Assignee: Ansaldo Energia Switzerland AGInventors: Oliver Joseph Taheny, Sven Olmes, Armin Busekros, Carlos Simon-Delgado, Daniel Jemora, Christophe Simonet, Luca Alberti, Eugenio Rossi
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Publication number: 20180347366Abstract: The present application provides a rotor for use in a turbine engine. The rotor may include a first rotor disc, a second rotor disc adjacent to the first rotor disc, and a belly band seal positioned between the first rotor disc and the second rotor disc. The belly band seal may include a band seal with a locking tab brazed thereon.Type: ApplicationFiled: April 25, 2018Publication date: December 6, 2018Inventors: Christophe Simonet, Marco Christof Pawlowski, Giovanni Cataldi
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Publication number: 20160333700Abstract: A method is disclosed for cooling a gas turbine having a turbine, wherein a rotor, which rotates about a machine axis, carries a plurality of rotating blades, which are mounted by blade roots and extend with their airfoils into a hot gas path of the gas turbine. The rotor is concentrically surrounded by a turbine vane carrier carrying a plurality of stationary vanes, whereby the rotating blades and the stationary vanes are arranged in alternating rows in axial direction. An extended lifetime with external cooling is achieved by providing first and second cooling systems for the turbine.Type: ApplicationFiled: May 13, 2016Publication date: November 17, 2016Applicant: ANSALDO ENERGIA SWITZERLAND AGInventors: Oliver Joseph TAHENY, Sven OLMES, Armin BUSEKROS, Carlos SIMON-DELGADO, Daniel JEMORA, Christophe SIMONET, Luca ALBERTI, Eugenio ROSSI
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Publication number: 20160177833Abstract: Disclosed is an engine, the engine having a compressor, an expansion machine, and a shaft, the shaft having a direction of rotation. The engine includes a compressed fluid main flow path, a flow divider arranged at and fluidly connected to the compressed fluid main flow path, and a duct fluidly connecting the flow divider and components of the expansion machine. The duct is arranged such that, when the engine is operated, a fluid is guided through the duct from the flow divider towards the expansion machine components. A flow deflector device is arranged within a flow path and configured to deflect and thereby accelerate a flow therethrough directed form the flow divider towards the expansion machine components in a tangential direction, wherein the deflection can be effected into the shaft direction of rotation.Type: ApplicationFiled: December 22, 2015Publication date: June 23, 2016Applicant: General Electric Technology GmbHInventors: Carlos SIMON-DELGADO, Oliver Joseph TAHENY, Sven OLMES, Armin BUSEKROS, Luca ALBERTI, Daniel JEMORA, Eugenio ROSSI, Christophe SIMONET
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Patent number: 9062551Abstract: A seal for reducing a fluid flow around tips of rotating blades of a turbine includes a plurality of diaphragms disposed in succession and providing an outer support for a radial arrangement of static blades disposed alternatingly with the rotating blades in an axial direction. An outer seal has axial and radial supports. The radial support includes a ring held in position by a key and a circumferential extension of the ring. The key and the circumferential extension have a clearance so as to allow a relative radial movement between the ring and a part of a casing or the plurality of diaphragms and providing a pressure sealing face and support in the axial direction.Type: GrantFiled: March 22, 2012Date of Patent: June 23, 2015Assignee: ALSTOM TECHNOLOGY LTDInventor: Christophe Simonet
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Patent number: 9057279Abstract: A labyrinth seal impedes leakage flow though a gap between confronting static and moving parts in a turbomachine. The seal includes axially spaced and circumferentially extending sealing fins arranged in leakage flow series and projecting across the gap from at least one of the confronting parts into sealing proximity with the opposing confronting part. The fins have at least a distal portion that is curved or inclined in the upstream direction of the leakage flow to deflect the leakage flow in the upstream direction. Successive fins define chambers that accommodate recirculating vortices produced by the deflected leakage flow.Type: GrantFiled: June 29, 2012Date of Patent: June 16, 2015Assignee: ALSTOM TECHNOLOGY LTDInventors: Osama Lotfi, Christophe Simonet, Niall Macdonald
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Publication number: 20130149118Abstract: A labyrinth seal impedes leakage flow though a gap between confronting static and moving parts in a turbomachine. The seal includes axially spaced and circumferentially extending sealing fins arranged in leakage flow series and projecting across the gap from at least one of the confronting parts into sealing proximity with the opposing confronting part. The fins have at least a distal portion that is curved or inclined in the upstream direction of the leakage flow to deflect the leakage flow in the upstream direction. Successive fins define chambers that accommodate recirculating vortices produced by the deflected leakage flow.Type: ApplicationFiled: June 29, 2012Publication date: June 13, 2013Applicant: ALSTOM TECHNOLOGY LTD.Inventors: Osama Lotfi, Christophe Simonet, Niall Macdonald
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Publication number: 20120243977Abstract: A seal for reducing a fluid flow around tips of rotating blades of a turbine includes a plurality of diaphragms disposed in succession and providing an outer support for a radial arrangement of static blades disposed alternatingly with the rotating blades in an axial direction. An outer seal has axial and radial supports. The radial support includes a ring held in position by a key and a circumferential extension of the ring. The key and the circumferential extension have a clearance so as to allow a relative radial movement between the ring and a part of a casing or the plurality of diaphragms and providing a pressure sealing face and support in the axial direction.Type: ApplicationFiled: March 22, 2012Publication date: September 27, 2012Applicant: ALSTOM Technology LtdInventor: Christophe Simonet