Patents by Inventor Frédéric DAUTREPPE
Frédéric DAUTREPPE 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: 12240618Abstract: A fan casing for an aircraft bypass turbojet engine includes one single wall configured to form at least one portion of an outer skin of a nacelle. The wall includes at least one reinforcement for stiffening the fan casing. The reinforcement is formed by a portion of the wall forming at least one annular area projecting towards an inside of the nacelle and/or having an overthickness. The reinforcement is further configured for fastening the fan casing to arms crossing a secondary stream flow path of the turbojet engine.Type: GrantFiled: December 13, 2021Date of Patent: March 4, 2025Assignee: Safran Aircraft EnginesInventors: Guillaume Glemarec, Quentin Matthias Emmanuel Garnaud, Frédéric Dautreppe
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Patent number: 12215631Abstract: An aircraft turbomachine module, including an accessory gearbox, a transfer shaft, and a drive shaft rotatably connected with one another by a power transmission device. The power transmission device can be housed in a gearbox and the module can further include an electric machine rotatably connected to the transfer shaft. The electric machine can be interposed between the transmission housing and at least one part the transfer shaft.Type: GrantFiled: December 20, 2021Date of Patent: February 4, 2025Assignee: SAFRAN AIRCRAFT ENGINESInventors: Frédéric Dautreppe, Jean-Pierre Elie Galivel
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Patent number: 12163475Abstract: Plate of pieces of hydraulic equipment of an aeronautical turbomachine comprising channels for circulation of fluids entering and leaving each of the pieces of hydraulic equipment, on the one hand further comprising a support part of a housing body of each of the pieces of hydraulic equipment intended to receive fastening means to these pieces of hydraulic equipment and on the other hand a housing body part of at least one of these pieces of hydraulic equipment.Type: GrantFiled: December 3, 2020Date of Patent: December 10, 2024Assignee: SAFRAN AIRCRAFT ENGINESInventors: Frédéric Dautreppe, Bertrand Romain Adrien Dufour, Romain Harold Patrice Pou
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Patent number: 12134983Abstract: A process for using an air input of a turboreactor nacelle of an aircraft, comprising an air input lip which comprises at least one fixed portion and at least one portion which can be moved between a first position, in which the air input lip has an aerodynamic profile so as to guide the internal air flow over the internal wall in order to promote a thrust phase, and a second position, in which the portion is displaced in relation to the fixed portion so that the air input lip has a second radial thickness in the second position which is less than the first radial thickness in the first position so as to promote a reverse thrust phase.Type: GrantFiled: April 8, 2020Date of Patent: November 5, 2024Assignee: SAFRAN AIRCRAFT ENGINESInventors: Daniel-Ciprian Mincu, Mathieu Patrick Jean-Louis Lallia, Nicolas Joseph Sirvin, Jagoda Alina Worotynska, Frederic Dautreppe, Anthony Binder, Eva Julie Lebeault
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Publication number: 20240229721Abstract: An accessory gearbox for an aircraft turbine engine having a radial shaft connecting a high-pressure body of the turbine engine to a gear train having at least one mixed shaft coupled to a high-speed device. The accessory gearbox has a clutch system having a low-speed motor mounted thereon and configured to mate with the mixed shaft such that: in an engaged position of the clutch, the low-speed motor is coupled to the mixed shaft so as to drive the high-pressure body at low speed when the turbine engine is stationary and, in a disengaged position of the clutch, the low-speed motor is decoupled from the mixed shaft so as to be protected when the turbine engine is in operation.Type: ApplicationFiled: February 24, 2022Publication date: July 11, 2024Applicant: SAFRAN AIRCRAFT ENGINESInventor: Frédéric Dautreppe
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Publication number: 20240133346Abstract: An accessory gearbox for an aircraft turbine engine having a radial shaft connecting a high-pressure body of the turbine engine to a gear train having at least one mixed shaft coupled to a high-speed device. The accessory gearbox has a clutch system having a low-speed motor mounted thereon and configured to mate with the mixed shaft such that: in an engaged position of the clutch, the low-speed motor is coupled to the mixed shaft so as to drive the high-pressure body at low speed when the turbine engine is stationary and, in a disengaged position of the clutch, the low-speed motor is decoupled from the mixed shaft so as to be protected when the turbine engine is in operation.Type: ApplicationFiled: February 24, 2022Publication date: April 25, 2024Applicant: SAFRAN AIRCRAFT ENGINESInventor: Frédéric Dautreppe
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Patent number: 11933246Abstract: An aircraft turbojet engine extending along an X axis and comprising a blower configured to provide a reverse thrust and a nacelle comprising an air intake which comprises at least one deflection member movably mounted between a deployed position in which the deflection member projects from the inner wall or from the lip of the air intake in a radially inward direction of deployment facing the X axis or in a longitudinal direction of deployment with respect to the X axis, in order to allow a release of the reverse air flow from the inner wall to support the reverse thrust phase, and a retracted position in which the air intake has an aerodynamic profile so as to guide the internal air flow along the inner wall in order to support the thrust phase.Type: GrantFiled: April 8, 2020Date of Patent: March 19, 2024Assignee: SAFRAN AIRCRAFT ENGINESInventors: Daniel-Ciprian Mincu, Jean-Loïc Hervé Lecordix, Nicolas Joseph Sirvin, Frédéric Dautreppe, Anthony Binder, Eva Julie Lebeault
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Publication number: 20240052789Abstract: An aircraft turbomachine module, including an accessory gearbox, a transfer shaft, and a drive shaft rotatably connected with one another by a power transmission device. The power transmission device can be housed in a gearbox and the module can further include an electric machine rotatably connected to the transfer shaft. The electric machine can be interposed between the transmission housing and at least one part the transfer shaft.Type: ApplicationFiled: December 20, 2021Publication date: February 15, 2024Applicant: SAFRAN AIRCRAFT ENGINESInventors: Frédéric DAUTREPPE, Jean-Pierre Elie GALIVEL
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Patent number: 11815027Abstract: The invention relates to a firewall (112) for a turbomachine (100) auxiliary arm (106). This firewall (112), which has one or more through openings (180) in a thickness direction (Z) of the firewall (112), comprises a fixed portion (120) and a first removable portion (130) extending, in a width direction (Y), orthogonal to said thickness direction (Z), from at least one adjacent opening among the through openings (180), to a first outer edge (190) of the firewall (112). To open this firewall (112) in order to allow access to one or more ducts and/or electrical cables (111) received in the through openings (180), the first removable portion (130) can be dismantled.Type: GrantFiled: May 12, 2020Date of Patent: November 14, 2023Assignee: SAFRAN AIRCRAFT ENGINESInventors: Romain Harold Patrice Pou, Frédéric Dautreppe, Bertrand Romain Adrien Dufour, Frédéric Jacques Eugène Goupil
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Patent number: 11739688Abstract: An aircraft turbojet engine comprising a fan configured to provide a reverse thrust and a nacelle comprising an air intake, the air intake comprising at least one circulation duct in the annular cavity opening, on the one hand, at the air intake lip and, on the other hand, at the inner wall and/or the outer wall so as to promote a reverse thrust phase, the air intake comprising at least one cover member mounted to move between a covered position, in which the cover member closes the circulation duct at the air intake lip and an uncovered position, in which the cover member opens the circulation duct at the air intake lip.Type: GrantFiled: April 8, 2020Date of Patent: August 29, 2023Assignee: Safran Aircraft EnginesInventors: Daniel-Ciprian Mincu, Mathieu Patrick Jean-Louis Lallia, Nicolas Joseph Sirvin, Jagoda Alina Worotynska, Frédéric Dautreppe
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Publication number: 20230184192Abstract: The invention relates to an exhaust case (15) for a turbomachine extending along a longitudinal axis (X), comprising: an annular shroud (23) having a wall (24) extending along the longitudinal axis (X) from a first flange (25), a plurality of openings (27) being provided through the wall (24); a plurality of mouths (28) each forming a channel (29) extending upstream to downstream between a respective inlet (30) and one of the openings (27), each mouth (28) having: a docking flange (31) at the inlet (30) having a radially inner edge (32) which is in contact with the first flange (25) of the annular shroud (23), a mouth wall (34) delimiting the channel (29) and comprising a radially inner wall portion (35) which is formed by a thickened section made on the wall (24) of the shroud (23).Type: ApplicationFiled: May 7, 2021Publication date: June 15, 2023Applicant: SAFRAN AIRCRAFT ENGINESInventors: Romain Harold Patrice POU, Frédéric DAUTREPPE
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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: 20230003235Abstract: Plate of pieces of hydraulic equipment of an aeronautical turbomachine comprising channels for circulation of fluids entering and leaving each of the pieces of hydraulic equipment, on the one hand further comprising a support part of a housing body of each of the pieces of hydraulic equipment intended to receive fastening means to these pieces of hydraulic equipment and on the other hand a housing body part of at least one of these pieces of hydraulic equipment.Type: ApplicationFiled: December 3, 2020Publication date: January 5, 2023Applicant: SAFRAN AIRCRAFT ENGINESInventors: Frédéric DAUTREPPE, Bertrand Romain Adrien DUFOUR, Romain Harold Patrice POU
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Publication number: 20220213839Abstract: The invention relates to a firewall (112) for a turbomachine (100) auxiliary arm (106). This firewall (112), which has one or more through openings (180) in a thickness direction (Z) of the firewall (112), comprises a fixed portion (120) and a first removable portion (130) extending, in a width direction (Y), orthogonal to said thickness direction (Z), from at least one adjacent opening among the through openings (180), to a first outer edge (190) of the firewall (112). To open this firewall (112) in order to allow access to one or more ducts and/or electrical cables (111) received in the through openings (180), the first removable portion (130) can be dismantled.Type: ApplicationFiled: May 12, 2020Publication date: July 7, 2022Applicant: SAFRAN AIRCRAFT ENGINESInventors: Romain Harold Patrice POU, Frédéric DAUTREPPE, Bertrand Romain Adrien DUFOUR, Frédéric Jacques Eugène GOUPIL
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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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Publication number: 20220186682Abstract: An aircraft turbojet engine extending along an X axis and comprising a blower configured to provide a reverse thrust and a nacelle comprising an air intake which comprises at least one deflection member movably mounted between a deployed position in which the deflection member projects from the inner wall or from the lip of the air intake in a radially inward direction of deployment facing the X axis or in a longitudinal direction of deployment with respect to the X axis, in order to allow a release of the reverse air flow from the inner wall to support the reverse thrust phase, and a retracted position in which the air intake has an aerodynamic profile so as to guide the internal air flow along the inner wall in order to support the thrust phase.Type: ApplicationFiled: April 8, 2020Publication date: June 16, 2022Applicant: SAFRAN AIRCRAFT ENGINESInventors: Daniel-Ciprian Mincu, Jean-Loïc Hervé Lecordix, Nicolas Joseph Sirvin, Frédéric Dautreppe, Anthony Binder, Eva Julie Lebeault
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Publication number: 20220170429Abstract: A process for using an air input of a turboreactor nacelle of an aircraft, comprising an air input lip which comprises at least one fixed portion and at least one portion which can be moved between a first position, in which the air input lip has an aerodynamic profile so as to guide the internal air flow over the internal wall in order to promote a thrust phase, and a second position, in which the portion is displaced in relation to the fixed portion so that the air input lip has a second radial thickness in the second position which is less than the first radial thickness in the first position so as to promote a reverse thrust phase.Type: ApplicationFiled: April 8, 2020Publication date: June 2, 2022Applicant: SAFRAN AIRCRAFT ENGINESInventors: Daniel-Ciprian Mincu, MATHIEU PATRICK JEAN-LOUIS LALLIA, NICOLAS JOSEPH SIRVIN, JAGODA ALINA WOROTYNSKA, FREDERIC DAUTREPPE, ANTHONY BINDER, EVA JULIE LEBEAULT
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Publication number: 20220170417Abstract: An aircraft turbojet engine comprising a fan configured to provide a reverse thrust and a nacelle comprising an air intake, the air intake comprising at least one circulation duct in the annular cavity opening, on the one hand, at the air intake lip and, on the other hand, at the inner wall and/or the outer wall so as to promote a reverse thrust phase, the air intake comprising at least one cover member mounted to move between a covered position, in which the cover member closes the circulation duct at the air intake lip and an uncovered position, in which the cover member opens the circulation duct at the air intake lip.Type: ApplicationFiled: April 8, 2020Publication date: June 2, 2022Applicant: SAFRAN AIRCRAFT ENGINESInventors: Daniel-Ciprian Mincu, Mathieu Patrick Jean-Louis Lallia, Nicolas Joseph Sirvin, Jagoda Alina Worotynska, Frédéric Dautreppe
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Publication number: 20220106049Abstract: A fan casing for an aircraft bypass turbojet engine includes one single wall configured to form at least one portion of an outer skin of a nacelle. The wall includes at least one reinforcement for stiffening the fan casing. The reinforcement is formed by a portion of the wall forming at least one annular area projecting towards an inside of the nacelle and/or having an overthickness. The reinforcement is further configured for fastening the fan casing to arms crossing a secondary stream flow path of the turbojet engine.Type: ApplicationFiled: December 13, 2021Publication date: April 7, 2022Applicant: SAFRAN AIRCRAFT ENGINESInventors: Guillaume GLEMAREC, Quentin Matthias Emmanuel GARNAUD, Frédéric DAUTREPPE
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Patent number: 9964041Abstract: A case structure interposed between the engine and the nacelle of the aircraft is provided. The case structure includes: a ferrule surrounding the engine and including a plurality of segments; at least one radial arm ensuring connection to the nacelle; and a plurality of attachment devices for securing the plurality of ferrule segments together or with at least one radial arm. The plurality of attachment devices includes an articulation device configured for ensuring coupling of the lifted-rotated-pushed type ensuring after disengagement of the ferrule segment, its pivoting about a pivot axis parallel to a longitudinal axis of the engine and then its blocking in a disengagement position.Type: GrantFiled: August 29, 2014Date of Patent: May 8, 2018Assignee: SNECMAInventors: Ceddric Beljambe, Frederic Dautreppe, Noel Robin