Patents by Inventor Josselin David Florian REGNARD
Josselin David Florian REGNARD 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: 11927133Abstract: An acoustic attenuation liner includes a porous coating with a mesh structure, an acoustically absorbent material covered with the porous coating and having a first volume, and at least one cavity created between the acoustically absorbent material and the porous coating and which has a second volume, such as Vcav>3%, wherein the mesh structure has wires separating between them openings passing through the structure, some of which have, when flat, a minimum elementary surface area.Type: GrantFiled: October 12, 2018Date of Patent: March 12, 2024Assignee: SAFRAN AIRCRAFT ENGINESInventors: Josselin David Florian Regnard, Norman Bruno André Jodet
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Patent number: 11873763Abstract: An acoustic treatment grid intended to be mounted inside or at the outlet of a duct of a bleed valve of a turbomachine of an aircraft intended to convey a gas flow, the grid comprising a perforated plate and circular orifices traversing the perforated plate along a first direction, the orifices having a diameter and a geometrical center. Each orifice is separated from an adjacent orifice by a space, the length of which is equal to the product of the diameter of said orifice and a spacing coefficient of a value between 1.1 and 6.Type: GrantFiled: April 7, 2021Date of Patent: January 16, 2024Assignees: SAFRAN AIRCRAFT ENGINES, ECOLE CENTRALE DE LYON, CENTRE NATIONAL DE LA RECHERCHE SCIENTIFIQUE, UNIVERSITE CLAUDE BERNARD LYON IInventors: Paul Clément Guillaume Laffay, Fernando Gea Aguilera, Josselin David Florian Regnard, Marc Cornelius Jacob, Stéphane Moreau
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Patent number: 11708790Abstract: Discharge grate intended to be mounted inside or at the outlet of a conduit of a discharge valve of a turbine engine of an aircraft, the discharge grate comprising an upstream face intended to receive a gas flow, a downstream face parallel to the upstream face and intended to deliver the gas flow received on the upstream face, and orifices passing through the perforated plate from the upstream face to the downstream face and intended to convey the gas flow through the perforated plate. The discharge grate comprises for each orifice of the perforated plate a tubular channel, coaxial with the orifice with which it is associated, and projecting from the downstream face of the perforated plate.Type: GrantFiled: April 6, 2021Date of Patent: July 25, 2023Assignees: SAFRAN AIRCRAFT ENGINES, ECOLE CENTRALE DE LYON, CENTRE NATIONAL DE LA RECHERCHE SCIENTIFIQUEInventors: Josselin David Florian Regnard, Paul Clément Guillaume Laffay, Marc Cornelius Jacob, Stéphane Moreau
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Publication number: 20230151769Abstract: An acoustic treatment grid intended to be mounted inside or at the outlet of a duct of a bleed valve of a turbomachine of an aircraft intended to convey a gas flow, the grid comprising a perforated plate and circular orifices traversing the perforated plate along a first direction, the orifices having a diameter and a geometrical center. Each orifice is separated from an adjacent orifice by a space, the length of which is equal to the product of the diameter of said orifice and a spacing coefficient of a value between 1.1 and 6.Type: ApplicationFiled: April 7, 2021Publication date: May 18, 2023Applicants: SAFRAN AIRCRAFT ENGINES, ECOLE CENTRALE DE LYON, CENTRE NATIONAL DE LA RECHERCHE SCIENTIFIQUE, UNIVERSITE CLAUDE BERNARD LYON IInventors: Paul Clément Guillaume LAFFAY, Fernando GEA AGUILERA, Josselin David Florian REGNARD, Marc Cornelius JACOB, Stéphane MOREAU
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Publication number: 20230124079Abstract: Discharge grate intended to be mounted inside or at the outlet of a conduit of a discharge valve of a turbine engine of an aircraft, the discharge grate comprising an upstream face intended to receive a gas flow, a downstream face parallel to the upstream face and intended to deliver the gas flow received on the upstream face, and orifices passing through the perforated plate from the upstream face to the downstream face and intended to convey the gas flow through the perforated plate. The discharge grate comprises for each orifice of the perforated plate a tubular channel, coaxial with the orifice with which it is associated, and projecting from the downstream face of the perforated plate.Type: ApplicationFiled: April 6, 2021Publication date: April 20, 2023Applicants: SAFRAN AIRCRAFT ENGINES, ECOLE CENTRALE DE LYON, CENTRE NATIONAL DE LA RECHERCHE SCIENTIFIQUE, UNIVERSITE CLAUDE BERNARD LYON IInventors: Josselin David Florian REGNARD, Paul Clément Guillaume LAFFAY, Marc Cornelius JACOB, Stéphane MOREAU
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Publication number: 20220412289Abstract: Resonating patch for acoustic treatment comprising a resonant plate, a transducer and an electrical circuit electrically connected to the transducer, the resonant plate comprising a peripheral strip extending along the perimeter of the resonant plate. The patch comprises cutouts together defining deformable lamellae having at least one end connected to the peripheral strip.Type: ApplicationFiled: November 19, 2020Publication date: December 29, 2022Applicants: SAFRAN AIRCRAFT ENGINES, CENTRE NATIONAL DE LA RECHERCHE SCIENTIFIQUE, UNIVERSITE DU MANSInventors: Josselin David Florian REGNARD, Thibault ABILY, Stéphane Bernard DURAND
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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: 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: 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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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: 20190112979Abstract: The invention relates to an acoustic attenuation liner comprising: a porous coating (39) with a mesh structure, an acoustically absorbent material (41) covered with the porous coating and having a first volume (Vabs) and at least one cavity (45) created between the acoustically absorbent material (41) and the porous coating (39) and which has a second volume (Vcav), such as Vcav>3% (Vcav+Vabs), wherein the mesh structure has wires (390) separating between them openings passing through said structure, some of which have, when flat, a minimum elementary area So.Type: ApplicationFiled: October 12, 2018Publication date: April 18, 2019Inventors: Josselin David Florian REGNARD, Norman Bruno André JODET
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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