Patents by Inventor Laurent Louis
Laurent Louis 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: 11912721Abstract: A series of fused pentacyclic imidazole derivatives, being potent modulators of human TNFa activity, are accordingly of benefit in the treatment and/or prevention of various human ailments, including autoimmune and inflammatory disorders; neurological and neurodegenerative disorders; pain and nociceptive disorders; cardiovascular disorders; metabolic disorders; ocular disorders; and oncological disorders. In particular, the present invention is concerned with 6, 7-dihydro-7, 14-methanobenzimidazo[1, 2-b][2,5]benzodiazocin-5(14H)-one derivatives and analogs thereof.Type: GrantFiled: November 24, 2020Date of Patent: February 27, 2024Assignees: UCB Biopharma SRL, SanofiInventors: Teresa De Haro Garcia, Michael Deligny, Jag Paul Heer, Joanna Rachel Quincey, Mengyang Xuan, Zhaoning Zhu, Daniel Christopher Brookings, Mark Daniel Calmiano, Yves Evrard, Martin Clive Hutchings, James Andrew Johnson, Sophie Jadot, Jean Keyaerts, Malcolm MacCoss, Matthew Duncan Selby, Michael Alan Shaw, Dominique Louis Leon Swinnen, Laurent Schio, Yann Foricher, Bruno Filoche-Romme
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Patent number: 11802511Abstract: Internal structure for a turbomachine nacelle, the internal structure being intended to surround at least one part of a compartment capable of receiving a gas generator of the turbomachine, the internal structure comprising a ventilation cavity of said compartment, the ventilation cavity being provided with a main ventilation outlet and an auxiliary ventilation outlet separate to the main ventilation outlet, the internal structure comprising a shut-off member movable relative to the ventilation cavity between a flow position and a shut-off position in which the shut-off member shuts off the auxiliary ventilation outlet to a greater extent than in the flow position.Type: GrantFiled: August 6, 2020Date of Patent: October 31, 2023Assignee: SAFRAN AIRCRAFT ENGINESInventors: Laurent Louis Robert Baudoin, Norman Bruno André Jodet
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Publication number: 20230213399Abstract: A hydraulic torque measurement device for an aircraft engine unit includes a hermetically sealed enclosure having a rigid wall and a deformable wall that define an internal volume. The device further includes at least one pressure measuring element capable of measuring the pressure prevailing in the internal volume. The hydraulic torque measuring device allows a service state in which the internal volume is filled exclusively with an incompressible liquid, and in which the deformable wall is configured to be subjected to a pressure force. In some embodiments, the hydraulic torque measurement device is suitable for use with a gearbox.Type: ApplicationFiled: May 9, 2021Publication date: July 6, 2023Applicant: SAFRAN HELICOPTER ENGINESInventor: Laurent Louis Sylvain HOUSSAYE
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Patent number: 11649765Abstract: Method for using an air intake of a turbojet engine nacelle comprising at least one elastically deformable portion, at least one connecting member mounted in an annular cavity integrally with the elastically deformable portion, and at least one controllable displacement member, in which method: during a thrust phase of the turbojet engine, the controllable displacement member moves the connecting member into a first position in which the elastically deformable portion of the air intake lip has an aerodynamic profile, and during a thrust reversal phase of the turbojet engine the controllable displacement member moves the connecting member into a second position in which the elastically deformable portion of the air intake lip has an irregular profile so as to allow a release of the reverse air flow from the elastically deformable portion.Type: GrantFiled: April 8, 2020Date of Patent: May 16, 2023Assignee: SAFRAN AIRCRAFT ENGINESInventors: Daniel-Ciprian Mincu, Laurent Louis Robert Baudoin, Nicolas Joseph Sirvin, Jagoda Alina Worotynska, Frédéric Dautreppe, Caroline Marie Frantz
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Publication number: 20220268212Abstract: Internal structure for a turbomachine nacelle, the internal structure being intended to surround at least one part of a compartment capable of receiving a gas generator of the turbomachine, the internal structure comprising a ventilation cavity of said compartment, the ventilation cavity being provided with a main ventilation outlet and an auxiliary ventilation outlet separate to the main ventilation outlet, the internal structure comprising a shut-off member movable relative to the ventilation cavity between a flow position and a shut-off position in which the shut-off member shuts off the auxiliary ventilation outlet to a greater extent than in the flow position.Type: ApplicationFiled: August 6, 2020Publication date: August 25, 2022Applicant: SAFRAN AIRCRAFT ENGINESInventors: Laurent Louis Robert BAUDOIN, Norman Bruno André JODET
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Publication number: 20220186663Abstract: Method for using an air intake of a turbojet engine nacelle comprising at least one elastically deformable portion, at least one connecting member mounted in an annular cavity integrally with the elastically deformable portion, and at least one controllable displacement member, in which method: during a thrust phase of the turbojet engine, the controllable displacement member moves the connecting member into a first position in which the elastically deformable portion of the air intake lip has an aerodynamic profile, and during a thrust reversal phase of the turbojet engine the controllable displacement member moves the connecting member into a second position in which the elastically deformable portion of the air intake lip has an irregular profile so as to allow a release of the reverse air flow from the elastically deformable portion.Type: ApplicationFiled: April 8, 2020Publication date: June 16, 2022Applicant: SAFRAN AIRCRAFT ENGINESInventors: Daniel-Ciprian Mincu, Laurent Louis Robert Baudoin, Nicolas Joseph Sirvin, Jagoda Alina Worotynska, Frédéric Dautreppe, Caroline Marie Frantz
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Patent number: 11000964Abstract: Device for perforating an acoustic annular panel for a turbine engine, wherein it includes a perforation needle support ring, the ring having an axis A of revolution and being intended to be inserted substantially coaxially inside the panel, the ring being sectored and including ring sectors regularly distributed around the axis and each one radially mobile opposite the axis from a radially inner rest position up to a perforation position of the radially outer panel, and at least one rotating actuator of rotation axis A and mechanically connected to the ring sectors such that a rotation of the actuator leads to a radial movement of the ring sectors.Type: GrantFiled: April 26, 2018Date of Patent: May 11, 2021Assignee: SAFRAN AIRCRAFT ENGINESInventors: Norman Bruno Andre Jodet, Laurent Louis Robert Baudoin, Jeremy Paul Gonzalez
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Patent number: 10927766Abstract: A turboprop including a propeller shaft and a gas generator running along this propeller shaft, this gas generator including a high-pressure shaft and a hollow low-pressure shaft both extending along the same longitudinal axis, the low-pressure shaft having a rear end coupled to a rear end of the propeller shaft via a reducer. It includes an accessory box contiguous to the reducer while being located facing a rear end of the low-pressure shaft, and coupled to the rear end of the high-pressure shaft by a shaft passing through the low-pressure shaft.Type: GrantFiled: November 9, 2017Date of Patent: February 23, 2021Assignee: SAFRAN AIRCRAFT ENGINESInventors: Nora El Ghannam, Geoffroy Marie Gerard Nicq, Mathieu Laurent Louis Perrier
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Patent number: 10837867Abstract: A ground testing device for a turbomachine, including an aircraft engine (12) extending axially from an air inlet to a nozzle, a shroud (20) having an axis of revolution (A) and surrounding at least partially the engine (12) so as to create an annular air flow between the engine (12) and the shroud (20) when the engine (12) is in operation, and a framework (22) allowing the shroud (20) to be supported.Type: GrantFiled: November 8, 2018Date of Patent: November 17, 2020Assignee: Safran Aircraft EnginesInventors: Laurent Louis Robert Baudoin, Josselin David Florian Regnard
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Patent number: 10787962Abstract: An aircraft propulsion unit including two distinct fan spools, and including a first duct and a second duct extending downstream of the two fan spools, the propulsion unit including a control ring disposed on one of the ducts, downstream of one of the fan spools, with at least one annular internal wall extending in an interior space of the duct, the control unit of the control ring being configured to modify the shape of the internal wall, and to cause an air passage cross section in the duct to vary at the ring, a device for acquiring acoustic signals generated by acoustic waves propagating downstream of the fan spools, and a device for processing the acoustic signals, configured to measure a dephasing between the acoustic waves and to control the control ring depending on the dephasing.Type: GrantFiled: July 31, 2018Date of Patent: September 29, 2020Assignee: Safran Aircraft EnginesInventors: Jean Michel Roux, Norman Bruno André Jodet, Laurent Louis Robert Baudoin
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Patent number: 10774745Abstract: The invention relates to an assembly for a turbine engine (1), the assembly including: a casing (20) extending along a longitudinal axis (X-X?) of the turbine engine (1), a surface heat exchanger (100) arranged along an inner edge (22) of said casing (20) and including a plurality of cooling fins (110) extending radially inwards and longitudinally, and a central body (30) partially concentrically arranged within said casing (20), said casing (20) and the central body (30) defining between one another an annular air channel (Va), the width (hVa) of which is substantially constant in the region of the heat exchanger (100). The assembly is characterized in that the fins (110) are distributed over more than 180° of the inner edge (22) of the casing (20) and in that the mean height ((hMOV) of the fins (110) is more than 5% of the width (hVa) of the annular air channel (Va) in the region the heat exchanger (100).Type: GrantFiled: January 25, 2017Date of Patent: September 15, 2020Assignee: SAFRAN AIRCRAFY ENGINESInventors: Josselin David Florian Regnard, Laurent Louis Robert Baudoin, Hélène Monique Orsi
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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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Patent number: 10578114Abstract: An assembly including a compressor for a turbine engine, and a discharge system including a supply duct, one end of which is connected to the compressor, the duct being configured to collect therefrom a flow of air compressed by the compressor; and a pressure-reduction device including an inlet and an outlet, the inlet being connected to the other end of the supply duct, wherein the pressure reduction device includes a casing forming a volume between the inlet and the outlet, a porous material occupying the volume, and a device for holding the porous material within the casing, wherein the outlet has an open section allowing the upper air to pass through the open section of the inlet.Type: GrantFiled: December 7, 2016Date of Patent: March 3, 2020Assignee: SAFRAN AIRCRAFT ENGINESInventors: Josselin David Florian Regnard, Laurent Louis Robert Baudoin
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Patent number: 10502134Abstract: The invention relates to an aircraft turbofan type engine (1) comprising an air intake duct (2) having an inner face provided with an acoustic attenuation shroud (11) located upstream from a fan (3) of this engine (1). This acoustic attenuation shroud (11) comprises a regular alternation of first portions and second portions with different first and second thicknesses along the radial direction, the number of alternations being greater than twice the number of passing azimuth acoustic vibration modes occurring in the engine (1) without the acoustic attenuation shroud (11) operating under conditions corresponding to a landing phase and a take-off phase.Type: GrantFiled: November 23, 2015Date of Patent: December 10, 2019Assignee: SAFRAN AIRCRAFT ENGINESInventors: Laurent Louis Robert Baudoin, Georges Jean Xavier Riou
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Publication number: 20190331028Abstract: A turboprop including a propeller shaft and a gas generator running along this propeller shaft, this gas generator including a high-pressure shaft and a hollow low-pressure shaft both extending along the same longitudinal axis, the low-pressure shaft having a rear end coupled to a rear end of the propeller shaft via a reducer. It includes an accessory box contiguous to the reducer while being located facing a rear end of the low-pressure shaft, and coupled to the rear end of the high-pressure shaft by a shaft passing through the low-pressure shaft.Type: ApplicationFiled: November 9, 2017Publication date: October 31, 2019Applicant: SAFRAN AIRCRAFT ENGINESInventors: Nora EL GHANNAM, Geoffroy Marie Gerard NICQ, Mathieu Laurent Louis PERRIER
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Publication number: 20190137362Abstract: A ground testing device for a turbomachine, including an aircraft engine (12) extending axially from an air inlet to a nozzle, a shroud (20) having an axis of revolution (A) and surrounding at least partially the engine (12) so as to create an annular air flow between the engine (12) and the shroud (20) when the engine (12) is in operation, and a framework (22) allowing the shroud (20) to be supported.Type: ApplicationFiled: November 8, 2018Publication date: May 9, 2019Applicant: SAFRAN AIRCRAFT ENGINESInventors: Laurent Louis Robert BAUDOIN, Josselin David Florian Regnard
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Publication number: 20190063314Abstract: An aircraft propulsion unit including two distinct fan spools, and including a first duct and a second duct extending downstream of the two fan spools, the propulsion unit including a control ring disposed on one of the ducts, downstream of one of the fan spools, with at least one annular internal wall extending in an interior space of the duct, the control unit of the control ring being configured to modify the shape of the internal wall, and to cause an air passage cross section in the duct to vary at the ring, a device for acquiring acoustic signals generated by acoustic waves propagating downstream of the fan spools, and a device for processing the acoustic signals, configured to measure a dephasing between the acoustic waves and to control the control ring depending on the dephasing.Type: ApplicationFiled: July 31, 2018Publication date: February 28, 2019Applicant: Safran Aircraft EnginesInventors: Jean Michel Roux, Norman Bruno Andre Jodet, Laurent Louis Robert Baudoin
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Publication number: 20190040795Abstract: The invention relates to an assembly for a turbine engine (1), the assembly including: a casing (20) extending along a longitudinal axis (X-X?) of the turbine engine (1), a surface heat exchanger (100) arranged along an inner edge (22) of said casing (20) and including a plurality of cooling fins (110) extending radially inwards and longitudinally, and a central body (30) partially concentrically arranged within said casing (20), said casing (20) and the central body (30) defining between one another an annular air channel (Va), the width (hVa) of which is substantially constant in the region of the heat exchanger (100). The assembly is characterized in that the fins (110) are distributed over more than 180° of the inner edge (22) of the casing (20) and in that the mean height ((hMOV) of the fms (110) is more than 5% of the width (hVa) of the annular air channel (Va) in the region the heat exchanger (100).Type: ApplicationFiled: January 25, 2017Publication date: February 7, 2019Applicant: SAFRAN AIRCRAFT ENGINESInventors: Josselin David Florian REGNARD, Laurent Louis Robert BAUDOIN, Hélène Monique ORSI
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Publication number: 20180355878Abstract: An assembly including a compressor for a turbine engine, and a discharge system including a supply duct, one end of which is connected to the compressor, the duct being configured to collect therefrom a flow of air compressed by the compressor; and a pressure-reduction device including an inlet and an outlet, the inlet being connected to the other end of the supply duct, wherein the pressure reduction device includes a casing forming a volume between the inlet and the outlet, a porous material occupying the volume, and a device for holding the porous material within the casing, wherein the outlet has an open section allowing the upper air to pass through the open section of the inlet.Type: ApplicationFiled: December 7, 2016Publication date: December 13, 2018Applicant: SAFRAN AIRCRAFT ENGINESInventors: Josselin David Florian REGNARD, Laurent Louis Robert BAUDOIN
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Publication number: 20180311859Abstract: Device for perforating an acoustic annular panel for a turbine engine, wherein it includes a perforation needle support ring, the ring having an axis A of revolution and being intended to be inserted substantially coaxially inside the panel, the ring being sectored and including ring sectors regularly distributed around the axis and each one radially mobile opposite the axis from a radially inner rest position up to a perforation position of the radially outer panel, and at least one rotating actuator of rotation axis A and mechanically connected to the ring sectors such that a rotation of the actuator leads to a radial movement of the ring sectors.Type: ApplicationFiled: April 26, 2018Publication date: November 1, 2018Inventors: Norman Bruno Andre JODET, Laurent Louis Robert BAUDOIN, Jeremy Paul GONZALEZ