Patents by Inventor Nathalie Nowakowski
Nathalie Nowakowski 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: 11891967Abstract: A turbofan includes a fan, a casing positioned downstream of the fan and separating a primary flowpath from a secondary flowpath, a compressor, a combustion chamber and a turbine being arranged in the primary flowpath, the turbofan having a differential transmission coupled to the turbine, and a power supply device configured to provide additional power to the one provided by the turbine to drive the compressor.Type: GrantFiled: September 20, 2019Date of Patent: February 6, 2024Assignee: SAFRAN AIRCRAFT ENGINESInventors: Henri Yesilcimen, Caroline Marie Frantz, Nicolas Jérôme Jean Tantot, Nathalie Nowakowski, Gilles Alain Marie Charier, Kévin Morgane Lemarchand, Jonathan Evert Vlastuin
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Patent number: 11421603Abstract: Turbojet engine includes a fan, a compressor, a combustion chamber, and a turbine configured to rotatably drive the fan via a first reduction gear and the compressor via a second reduction gear, in which an outlet of the first reduction gear is rotatably coupled to an inlet of the second reduction gear by a reduction shaft, the reduction shaft being supported by a bearing arranged between the first reduction gear and the second reduction gear.Type: GrantFiled: September 20, 2019Date of Patent: August 23, 2022Assignee: SAFRAN AIRCRAFT ENGINESInventors: Nathalie Nowakowski, Gilles Alain Marie Charier, Kévin Morgane Lemarchand, Nicolas Jérôme Jean Tantot, Jonathan Evert Vlastuin, Henri Yesilcimen
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Patent number: 11313325Abstract: A turbofan having a dilution rate of at least 10 and including a fan having a disc provided with blades at the periphery thereof, a distance between the head of the blades and the housing of the fan being less than or equal to ten millimeters; a primary flow space and secondary flow space that are concentric; a turbine, housed in the primary flow space and in fluid communication with the fan; and a reduction mechanism coupling the turbine and the fan.Type: GrantFiled: March 15, 2017Date of Patent: April 26, 2022Assignee: Safran Aircraft EnginesInventors: Jeremy Dievart, Yanis Benslama, Nathalie Nowakowski
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Patent number: 11268450Abstract: A turbomachine comprising a ducted fan, a low-pressure turbine shaft and a reduction gearbox housed in a casing between the fan and the low-pressure turbine shaft, the fan rotor supplying airflow to a primary stream and a secondary stream and comprising a hub of diameter D1, wherein—the diameter D3 of the fan rotor is greater than 82 inches (2.08 metres), —the pressure ratio of the fan is between 1.10 and 1.35, the turbomachine comprises a low-pressure compressor separate from the fan, the reduction gearbox being interposed between the fan rotor and a turbine shaft of the low-pressure compressor, and wherein the reduction gearbox casing has an outside diameter D2 greater than the diameter D1 of the hub, the pitch diameter D4 of the reduction gearbox ring being between 0.15 and 0.35 times the fan rotor diameter.Type: GrantFiled: May 2, 2018Date of Patent: March 8, 2022Assignee: SAFRAN AIRCRAFT ENGINESInventors: Kevin Morgane Lemarchand, Gilles Alain Marie Charier, Nathalie Nowakowski, Nicolas Jérôme Jean Tantot, Matthieu Pierre Michel Dubosc, Dominique Gerhardt Mayhew
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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: 11174781Abstract: The present invention relates to a powerplant of an aircraft including at least one twin-spool gas generator of longitudinal axis (XX), at least one main fan arranged upstream of the gas generator on the longitudinal axis (XX) and driven in rotation by the gas generator, the main fan being shrouded with a main fan housing; and at least one auxiliary fan with axis (XY, XY?) offset relative to the longitudinal axis (XX) and driven by the gas generator, the auxiliary fan being shrouded with an auxiliary fan housing, the gas generator including at least one low-pressure compressor and a low-pressure turbine connected by a low-pressure shaft, the low-pressure turbine driving in rotation the main fan and the auxiliary fan via at least one power transmission system including a differential gear system incorporating a bevel gear.Type: GrantFiled: October 5, 2016Date of Patent: November 16, 2021Assignee: SAFRAN AIRCRAFT ENGINESInventors: Laurent Soulat, Kevin Morgane Lemarchand, Tewfik Boudebiza, Gilles Alain Charier, Nathalie Nowakowski, Augustin Marc Michel Curlier, Adrien Pierre Jean Pertat, Pierre-Alain Jean Philippe Reigner
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Publication number: 20210348566Abstract: Turbojet engine includes a fan, a compressor, a combustion chamber, and a turbine configured to rotatably drive the fan via a first reduction gear and the compressor via a second reduction gear, in which an outlet of the first reduction gear is rotatably coupled to an inlet of the second reduction gear by a reduction shaft, the reduction shaft being supported by a bearing arranged between the first reduction gear and the second reduction gear.Type: ApplicationFiled: September 20, 2019Publication date: November 11, 2021Applicant: SAFRAN AIRCRAFT ENGINESInventors: Nathalie NOWAKOWSKI, Gilles Alain Marie CHARIER, Kévin Morgane LEMARCHAND, Nicolas Jérôme Jean TANTOT, Jonathan Evert VLASTUIN, Henri YESILCIMEN
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Publication number: 20210317800Abstract: A turbofan includes a fan, a casing positioned downstream of the fan and separating a primary flowpath from a secondary flowpath, a compressor, a combustion chamber and a turbine being arranged in the primary flowpath, the turbofan having a differential transmission coupled to the turbine, and a power supply device configured to provide additional power to the one provided by the turbine to drive the compressor.Type: ApplicationFiled: September 20, 2019Publication date: October 14, 2021Applicant: SAFRAN AIRCRAFT ENGINESInventors: Henri YESILCIMEN, Caroline Marie FRANTZ, Nicolas Jérôme Jean TANTOT, Nathalie NOWAKOWSKI, Gilles Alain Marie CHARIER, Kévin Morgane LEMARCHAND, Jonathan Evert VLASTUIN
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Patent number: 11059597Abstract: An aircraft including a fuselage, a lateral support wing (1) and a propulsion assembly (100) mounted under the wing. The wing includes at least two structural spars (11ba, 11bf) extending from the fuselage toward the tip of the wing, one of these (11ba) being upstream and the other (11bf) downstream. The propulsion assembly includes a gas generator (106) and at least two offset fans (102, 104) arranged on either side of the axis of the gas generator. The offset fans (102, 104) are attached directly to one of the spars (11ba, 11bf) and the gas generator (106) is attached directly to the two spars. The leading edge of the wing forms a given sweep of angle (?) with the axis of the fuselage. The two offset fans (102, 104) are axially offset from one another.Type: GrantFiled: September 29, 2016Date of Patent: July 13, 2021Assignee: SAFRAN AIRCRAFT ENGINESInventors: Bruno Albert Beutin, Nicolas Maurice Herve Aussedat, Nicolas Alain Bader, Philippe Gerard Chanez, Gilles Alain Charier, Mathieu Lallia, Lionel Jean Leon Lefranc, Kevin Morgane Lemarchand, Herve Jean Albert Mouton, Nicolas Joseph Sirvin, Ludovic Michael Laurent Toupet, Christian Sylvain Vessot, Nathalie Nowakowski
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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: 11047338Abstract: A turbofan engine including: a turbine shaft; a fan shaft; and a reduction mechanism coupling the turbine shaft and the fan shaft, is provided. The turbofan engine has a bypass ratio greater than or equal to 10, and the turbine shaft is supported by four bearings such that the flexural deformation modes of the turbine shaft are positioned in transient phase or outside the operating range of the turbofan engine.Type: GrantFiled: March 15, 2017Date of Patent: June 29, 2021Assignee: Safran Aircraft EnginesInventors: Jeremy Dievart, Yanis Benslama, Nathalie Nowakowski
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Patent number: 11015521Abstract: An aircraft propulsion assembly comprising at least a main turbine mounted along a longitudinal axis, at least one main fan arranged upstream of the main turbine along the longitudinal axis and driven in rotation by the said main turbine, the said main fan being ducted by a main fan casing, an auxiliary turbine mounted along the longitudinal axis, the auxiliary turbine being independent of the main turbine, an auxiliary fan of axis offset with respect to the longitudinal axis and driven by the auxiliary turbine, the auxiliary fan being ducted by an auxiliary fan casing, the main casing being separate and distinct from the auxiliary casing so as respectively to generate a main secondary flow and an auxiliary secondary flow which remain independent of one another until they are discharged into the atmosphere.Type: GrantFiled: October 5, 2016Date of Patent: May 25, 2021Assignee: SAFRAN AIRCRAFT ENGINESInventors: Augustin Marc Michel Curlier, Adrien Pierre Jean Pertat, Pierre-Alain Jean Philippe Reigner, Laurent Soulat, Kevin Morgane Lemarchand, Tewfik Boudebiza, Gilles Alain Charier, 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: 10895200Abstract: An aircraft turbine engine includes a fan and a reduction gear including a plurality of rotary elements and driving the fan. The turbine engine further includes a gearbox and a mechanical power takeoff box driving the gearbox. The turbine engine includes a first toothed wheel and a second toothed wheel forming part of the mechanical power takeoff box and meshing with the first toothed wheel.Type: GrantFiled: April 27, 2015Date of Patent: January 19, 2021Assignee: SAFRAN AIRCRAFT ENGINESInventors: Nathalie Nowakowski, Thomas Alain Christian Vincent
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Patent number: 10850859Abstract: An aircraft includes a wing having a first upstream spar and a second downstream spar extending in the direction of the span of said wing, and at least one propulsion unit supported by the wing. The propulsion unit includes a turboprop engine and a propeller. The propeller includes an external annular casing fixed to a suction surface of the wing, and at least to the first upstream spar via at least one first and second fastener.Type: GrantFiled: October 4, 2016Date of Patent: December 1, 2020Assignee: Safran Aircraft EnginesInventors: Kevin Morgane Lemarchand, Tewfik Boudebiza, Gilles Alain Charier, Nathalie Nowakowski
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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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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