Patents by Inventor Nils Edouard Romain BORDONI
Nils Edouard Romain BORDONI 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: 11230978Abstract: Aircraft turbine engine, including at least one first compressor, an annular combustion chamber and at least one first turbine, which define a first flow duct for a primary flow. Between the combustion chamber and the first turbine is a device for discharging at least part of the primary flow.Type: GrantFiled: March 30, 2017Date of Patent: January 25, 2022Assignee: SAFRAN AIRCRAFT ENGINESInventors: Arnaud Nicolas Negri, Nils Edouard Romain Bordoni, Michel Gilbert Rolland Brault, Guillaume Patrice Kubiak, Nathalie Nowakowski, Romain Guillaume Cuvillier
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Patent number: 11149566Abstract: A guide vane in an outer section of a turbofan engine contains oil cooling cavities which are located on one side of a main bending axis of the vane so that the differential thermal expansions compensate for the bending deformations caused by the aerodynamic forces exerted on the outer vane surface.Type: GrantFiled: December 17, 2018Date of Patent: October 19, 2021Assignee: SAFRAN AIRCRAFT ENGINESInventor: Nils Edouard Romain Bordoni
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Patent number: 11053852Abstract: A multi-flow turbojet engine generally includes an upstream ducted fan driven by a gas generator, the gas generator having a first and a second compressor, which are coaxial, an inlet case forming a support for the rotors of the upstream ducted fan and of the first compressor, an inter-compressor case downstream of the inlet casing and forming a support for the rotors of the second compressor, attachment means for thrust take-up rods, which attachment means are arranged on the inter-compressor case. The turbojet engine includes at least one axial stress transmission rod for connecting the inlet case to the inter-compressor case.Type: GrantFiled: December 12, 2016Date of Patent: July 6, 2021Assignee: SAFRAN AIRCRAFT ENGINESInventors: Nils Edouard Romain Bordoni, Michel Gilbert Roland Brault, Romain Guillaume Cuvillier, Guillaume Patrice Kubiak, Arnaud Nicolas Negri, Nathalie Nowakowski
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Patent number: 10975725Abstract: A turbofan including a low-pressure shaft; a high-pressure shaft; a fan shaft; a reducing mechanism that couples the low-pressure shaft to the fan shaft; and a maximum of six chambers that accommodate the bearings of the low-pressure shaft, the bearings of the high-pressure shaft and the bearings of the fan as well as the reducing mechanism.Type: GrantFiled: March 15, 2017Date of Patent: April 13, 2021Assignee: Safran Aircraft EnginesInventors: Romain Guillaume Cuvillier, Nils Edouard Romain Bordoni, Michel Gilbert Roland Brault, Jeremy Dievart, Guillaume Patrice Kubiak, Arnaud Nicolas Negri, Nathalie Nowakowski
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Patent number: 10907486Abstract: A turbomachine module includes a rotor supporting variable pitch blades, and an inner annular shaft, a blade pitch control device, a device for feathering at least one blade comprising at least one gas generator placed between a body and a movable member. The control device and the feathering device are situated radially between the shaft and the blades, the movable member is coupled with the at least one blade and capable, under the action of the gas generated and/or released by the generator, of being moved into a reference position wherein it entails a feathered position to the at least one blade.Type: GrantFiled: May 17, 2018Date of Patent: February 2, 2021Assignee: SAFRAN AIRCRAFT ENGINESInventors: Nils Edouard Romain Bordoni, Michel Gilbert Roland Brault, Romain Guillaume Cuvillier, Guillaume Patrice Kubiak, Arnaud Nicolas Negri, Nathalie Nowakowski
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Patent number: 10859000Abstract: The invention relates to a system for rotating a fan (2) of a turbojet engine (1) about a first rotation axis ?, including a reduction gear (3) made up of a planetary gearset placed at the centre of the fan (2), which includes: a central sun gear (31); an outer planet gear (33) attached to the fan (2); at least one satellite gear (32) arranged between the central sun gear (31) and the outer planet gear (33) in order to transmit a rotary movement between the central sun gear (31) and the outer planet gear (33); characterised in that the outer planet gear (33) includes an inner portion (33a) which meshes with the satellite gear (32), as well as an outer portion (33b) to which blades (21) of the fan (2) are directly attached.Type: GrantFiled: February 8, 2017Date of Patent: December 8, 2020Assignee: SAFRAN AIRCRAFT ENGINESInventors: Guillaume Patrice Kubiak, Nils Edouard Romain Bordoni, Michel Gilbert Roland Brault, Romain Guillaume Cuvillier, Benoit Jean Henri Gomanne, Arnaud Nicolas Negri, Nicolas Xavier Trappier
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Patent number: 10837317Abstract: A bypass turbojet engine including a low pressure shaft supported by at least two low pressure bearings, a high pressure shaft supported by at least two high pressure bearings, a fan shaft supported by at least two fan bearings, a reduction system coupling the low pressure shaft, with the fan shaft, enclosures housing the low pressure bearings, the high pressure bearings, the fan bearings and the reduction system, and a lubrication assembly including a closed oil circuit configured to supply oil to the enclosures in order to cool the bearings and the reduction system and at most five recovery pumps configured to recover oil from the enclosures.Type: GrantFiled: March 15, 2017Date of Patent: November 17, 2020Assignee: Safran Aircraft EnginesInventors: Romain Guillaume Cuvillier, Nils Edouard Romain Bordoni, Michel Gilbert Roland Brault, Sebastien Christophe Chalaud, Guillaume Patrice Kubiak, Arnaud Nicolas Negri, Nathalie Nowakowski
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Patent number: 10830066Abstract: A fan of a turbine engine includes a disc provided with blades at the periphery thereof, the blades being mounted so as to pivot on the disc about a pivot axis, and a mechanism for changing the pitch of the blades. The mechanism is configured to adjust an angular position of each blade around the pivot axis. The angular position is in an angular setting range no greater than 20°.Type: GrantFiled: January 5, 2017Date of Patent: November 10, 2020Assignee: Safran Aircraft EnginesInventors: Romain Guillaume Cuvillier, Nils Edouard Romain Bordoni, Michel Gilbert Roland Brault, Guillaume Patrice Kubiak, Arnaud Nicolas Negri, Nathalie Nowakowski, Emmanuel Pierre Dimitri Patsouris, Sebastien Emile Philippe Tajan
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Publication number: 20200347737Abstract: A guide vane in an outer section of a turbofan engine contains oil cooling cavities which are located on one side of a main bending axis of the vane so that the differential thermal expansions compensate for the bending deformations caused by the aerodynamic forces exerted on the outer vane surface.Type: ApplicationFiled: December 17, 2018Publication date: November 5, 2020Applicant: SAFRAN AICRFT ENGINESInventor: Nils Edouard Romain BORDONI
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Patent number: 10815892Abstract: A multiflow turbojet engine generally includes an upstream fan driven by a gas generator having first and second coaxial compressors, an intake case forming a mounting for the rotors of the upstream fan and the first compressor, an inter-compressor case downstream from the intake case and forming a mounting for the rotors of the second compressor, and attachment means for thrust take-up control rods arranged in the inter-compressor case. The turbojet engine also includes a structural force shroud connecting the intake case to the inter-compressor case, of the and a floating first compressor case.Type: GrantFiled: December 12, 2016Date of Patent: October 27, 2020Assignee: SAFRAN AIRCRAFT ENGINESInventors: Michel Gilbert Roland Brault, Nils Edouard Romain Bordoni, Romain Guillaume Cuvillier, Guillaume Patrice Kubiak, Arnaud Nicolas Negri, Nathalie Nowakowski
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Device for limiting overspeeding of a turbine shaft of a turbomachine, and associated control method
Patent number: 10781714Abstract: Embodiments of the disclosure relate to a device for limiting overspeeding of a turbine shaft of a turbomachine, comprising structure for destroying the rotor blades of at least one turbine stage. The structure includes a casing and at least one projectile configured for projecting into the path of the rotor blades of the stage in order for the stage in question to be destroyed.Type: GrantFiled: March 29, 2017Date of Patent: September 22, 2020Assignee: SAFRAN AIRCRAFT ENGINESInventors: Arnaud Nicolas Negri, Nils Edouard Romain Bordoni, Michel Gilbert Roland Brault, Romain Guillaume Cuvillier, Guillaume Patrice Kubiak, Nathalie Nowakowski -
Patent number: 10773813Abstract: The present invention relates to an aircraft comprising a fuselage (1) and a propulsion unit at the rear of the fuselage, the propulsion unit comprising at least one fan rotor (7, 8), a nacelle (14) fairing the fan and at least one connection means (15) connecting the nacelle to the fuselage, the fan being rotated by the energy supplied by at least one gas-turbine gas generator (2a, 2b) housed in the fuselage, said gas generator comprising auxiliary equipment cooled by a cooling circuit. The aircraft is characterised in that said cooling circuit comprises at least one heat exchanger exchanging heat with the ambient air housed in one of said connection means (15) and/or in said nacelle (14). The cooling circuit optionally comprises also a heat exchanger exchanging heat with the ambient air, housed in the tail unit.Type: GrantFiled: July 21, 2016Date of Patent: September 15, 2020Assignee: SAFRAN AIRCRAFT ENGINESInventors: Nils Edouard Romain Bordoni, Antoine Jean-Philippe Beaujard, Nicolas Jerome Jean Tantot
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Publication number: 20200191055Abstract: A twin-spool turbojet engine includes: a low-pressure spool having a low-pressure compressor, a low-pressure turbine, and a low-pressure shaft connecting the low-pressure turbine to the low-pressure compressor; an exhaust casing through which exhaust gases flow downstream of the low-pressure turbine; and a low-pressure shaft thrust bearing having an inner ring and an outer ring, one of the rings being fastened on the low-pressure shaft and the other of the rings being fastened on the exhaust casing.Type: ApplicationFiled: August 24, 2018Publication date: June 18, 2020Applicant: SAFRAN AIRCRAFT ENGINESInventors: Guillaume Patrice KUBIAK, Nils Edouard Romain BORDONI, Michel Gibert Roland BRAULT, Romain Guillaume CUVILLIER, Arnaud Nicolas NEGRI, Nathalie NOWAKOWSKI
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Patent number: 10662776Abstract: An assembly includes a one-piece bladed disk, at least one low-pressure compressor rotor, and a low-pressure compressor shaft. The bladed disk and the low-pressure compressor rotor are both adapted to be shrunk onto the low-pressure compressor shaft and mechanically attached to it by sets of splines. At least one clamping member blocks axially the different collars with respect to the shaft.Type: GrantFiled: May 21, 2018Date of Patent: May 26, 2020Assignee: SAFRAN AIRCRAFT ENGINESInventors: Mathieu Laurent Louis Perrier, Nils Edouard Romain Bordoni, Gilles Alain Marie Charier
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Publication number: 20200095876Abstract: A fan of a turbine engine includes a disc provided with blades at the periphery thereof, the blades being mounted so as to pivot on the disc about a pivot axis, and a mechanism for changing the pitch of the blades. The mechanism is configured to adjust an angular position of each blade around the pivot axis. The angular position is in an angular setting range no greater than 20°.Type: ApplicationFiled: January 5, 2017Publication date: March 26, 2020Applicant: Safran Aircraft EnginesInventors: Romain Guillaume CUVILLIER, Nils Edouard Romain BORDONI, Michel Gilbert Roland BRAULT, Guillaume Patrice KUBIAK, Arnaud Nicolas NEGRI, Nathalie NOWAKOWSKI, Emmanuel Pierre Dimitri PATSOURIS, Sebastien Emile Philippe TAJAN
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DEVICE FOR LIMITING OVERSPEEDING OF A TURBINE SHAFT OF A TURBOMACHINE, AND ASSOCIATED CONTROL METHOD
Publication number: 20190277156Abstract: Embodiments of the disclosure relate to a device for limiting overspeeding of a turbine shaft of a turbomachine, comprising structure for destroying the rotor blades of at least one turbine stage. The structure includes a casing and at least one projectile configured for projecting into the path of the rotor blades of the stage in order for the stage in question to be destroyed.Type: ApplicationFiled: March 29, 2017Publication date: September 12, 2019Applicant: SAFRAN AIRCRAFT ENGINESInventors: Arnaud Nicolas Negri, Nils Edouard Romain Bordoni, Michel Gilbert Roland Brault, Romain Guillaume Cuvillier, Guillaume Patrice Kubiak, Nathalie Nowakowski -
Patent number: 10316857Abstract: A fan of a turbine engine, the fan including a fan disk provided with blades on its periphery, the blades being pivotally mounted on the disk around a pivoting axis and having a center of gravity, and a pitch change mechanism for the blades, each blade being configured so that its center of gravity is positioned on or at a small distance from a fictitious plane which passes through the pivoting axis of the blade and which is perpendicular to the axis of revolution of the fan when the blade is in a minimum drag position.Type: GrantFiled: January 4, 2017Date of Patent: June 11, 2019Assignee: SAFRAN AIRCRAFT ENGINESInventors: Nils Edouard Romain Bordoni, Michel Gilbert Roland Brault, Romain Guillaume Cuvillier, Guillaume Patrice Kubiak, Arnaud Nicolas Negri, Nathalie Nowakowski
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Publication number: 20190153958Abstract: The invention relates to a system for rotating a fan (2) of a turbojet engine (1) about a first rotation axis ?, including a reduction gear (3) made up of a planetary gearset placed at the centre of the fan (2), which includes: a central sun gear (31); an outer planet gear (33) attached to the fan (2); at least one satellite gear (32) arranged between the central sun gear (31) and the outer planet gear (33) in order to transmit a rotary movement between the central sun gear (31) and the outer planet gear (33); characterised in that the outer planet gear (33) includes an inner portion (33a) which meshes with the satellite gear (32), as well as an outer portion (33b) to which blades (21) of the fan (2) are directly attached.Type: ApplicationFiled: February 8, 2017Publication date: May 23, 2019Applicant: SAFRAN AIRCRAFT ENGINESInventors: Guillaume Patrice KUBIAK, Nils Edouard Romain BORDONI, Michel Gilbert Roland BRAULT, Romain Guillaume CUVILLIER, Benoit Jean Henri GOMANNE, Arnaud Nicolas NEGRI, Nicolas Xavier TRAPPIER
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Publication number: 20190101081Abstract: A bypass turbojet engine including a low pressure shaft supported by at least two low pressure bearings, a high pressure shaft supported by at least two high pressure bearings, a fan shaft supported by at least two fan bearings, a reduction system coupling the low pressure shaft, with the fan shaft, enclosures housing the low pressure bearings, the high pressure bearings, the fan bearings and the reduction system, and a lubrication assembly including a closed oil circuit configured to supply oil to the enclosures in order to cool the bearings and the reduction system and at most five recovery pumps configured to recover oil from the enclosures.Type: ApplicationFiled: March 15, 2017Publication date: April 4, 2019Applicant: Safran Aircraft EnginesInventors: Romain Guillaume CUVILLIER, Nils Edouard Romain BORDONI, Michel Gilbert Roland BRAULT, Sebastien Christophe CHALAUD, Guillaume Patrice KUBBIAK, Arnaud Nicolas NEGRI, Nathalie NOWAKOWSKI
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Publication number: 20190085724Abstract: A turbofan including a low-pressure shaft; a high-pressure shaft; a fan shaft; a reducing mechanism that couples the low-pressure shaft to the fan shaft; and a maximum of six chambers that accommodate the bearings of the low-pressure shaft, the bearings of the high-pressure shaft and the bearings of the fan as well as the reducing mechanism.Type: ApplicationFiled: March 15, 2017Publication date: March 21, 2019Applicant: Safran Aircraft EnginesInventors: Romain Guillaume CUVILLIER, Nils Edouard Romain BORDONI, Michel Gilbert Roland BRAULT, Jeremy DIEVART, Guillaume Patrice KUBIAK, Arnaud Nicolas NEGRI, Nathalie NOWAKOWSKI