Patents by Inventor Vivien Mickael COURTIER
Vivien Mickael COURTIER 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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Publication number: 20220333493Abstract: Fibrous preform for a composite blade and also a composite blade formed by means of such a preform, a rotor and a rotating machine comprising such a blade, the preform comprising a first longitudinal section, configured to form a blade root, and a second longitudinal section, extending from the first longitudinal section, configured to form a portion of an airfoil, wherein the first longitudinal section has a first thickness at its upper end and wherein the second longitudinal section comprises at least one set-back zone having a thickness at least three times less than the first thickness, said set-back zone occupying at least 50% of the second longitudinal section.Type: ApplicationFiled: September 2, 2020Publication date: October 20, 2022Applicant: SAFRAN AIRCRAFT ENGINESInventors: Vivien Mickaël COURTIER, Dominique Gerhardt MAYHEW, Adrien Jacques Philippe FABRE, Adrien Louis Nicolas LAURENCEAU
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Patent number: 11473430Abstract: The invention relates to a turbomachine assembly (1) comprising a fan (2) and a booster drum-type part (3), the fan (2) comprising:—blades (20) comprising an airfoil (23) and an extension (30) mounted on and attached to the trailing edge (25) of the airfoil (23),—a fan (2) disc (10) and—a series of inter-blade platforms (16), the extension (30) of each blade (20) extending beyond the downstream face (14) of the fan (2) disc (10) in the direction of the upstream edge (4) of the part (3) and covering, at least partially, the cavity (6) between the fan (2) and the part (3).Type: GrantFiled: December 20, 2019Date of Patent: October 18, 2022Assignee: SAFRAN AIRCRAFT ENGINESInventors: Paul Antoine Foresto, Vivien Mickaël Courtier, Stéphane Roger Mahias, William Henri Joseph Riera
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Publication number: 20220268159Abstract: The present invention relates to a blower vane of a turbomachine, comprising a structure made of composite material which comprises a fibrous reinforcement and a matrix in which the fibrous reinforcement is embedded. The vane comprises a first rigidification insert which extends in a first direction and at least one second insert which is connected to the first in a second direction which is non-collinear with the first direction, the first insert projecting from the vane in order to be connected to a disc of a turbomachine element.Type: ApplicationFiled: July 9, 2020Publication date: August 25, 2022Applicant: Safran Aircraft EnginesInventors: Clément Pierre POSTEC, Vivien Mickaël COURTIER, Vincent JOUDON
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Patent number: 11401823Abstract: An aviation turbine engine having at least one unducted rotary propeller having a plurality of blades, each blade including: a blade body made of composite material including fiber reinforcement densified by a matrix, the fiber reinforcement of the blade body presenting three-dimensional weaving, the body extending between a leading edge and a trailing edge, and a protective fitting for protecting the leading edge and made of composite material having fiber reinforcement densified by a matrix, the fitting being adhesively bonded onto the leading edge of the blade body, the fitting being formed from a dry fiber preform injection molded with a densifying resin, and a polyurethane film for providing protection against erosion covering the blade body and the fitting.Type: GrantFiled: March 17, 2017Date of Patent: August 2, 2022Assignee: SAFRAN AIRCRAFT ENGINESInventors: Adrien Jacques Philippe Fabre, Vivien Mickaël Courtier, Adrien Louis Nicolas Laurenceau, Dominique Gerhadt Mayhew
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Publication number: 20220097824Abstract: A blade includes a fibrous reinforcement having a three-dimensional weave densified by a matrix, the fibrous reinforcement including, in a single woven piece, a root and an aerodynamic profile part extending along a longitudinal direction between the root part and a blade tip portion and along a transverse direction between a leading and a trailing edge portion. The profile part includes first and second suction side and pressure side faces. The fibrous reinforcement includes a separation forming a housing inside the fibrous reinforcement, a bladder filled with a shaping foam being present in the housing. The separation extends over a separation zone inside the profile part of the fibrous reinforcement comprised between the root part and the blade tip portion in the longitudinal direction and between the leading and the trailing edge portion in the transverse direction. The separation opens to the outside of the profile part.Type: ApplicationFiled: January 3, 2020Publication date: March 31, 2022Inventors: Vivien Mickaël COURTIER, Dominique Gerhardt MAYHEW, Adrien Louis Nicolas LAURENCEAU
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Publication number: 20220056803Abstract: The invention relates to a turbomachine assembly (1) comprising a fan (2) and a booster drum-type part (3), the fan (2) comprising:—blades (20) comprising an airfoil (23) and an extension (30) mounted on and attached to the trailing edge (25) of the airfoil (23),—a fan (2) disc (10) and—a series of inter-blade platforms (16), the extension (30) of each blade (20) extending beyond the downstream face (14) of the fan (2) disc (10) in the direction of the upstream edge (4) of the part (3) and covering, at least partially, the cavity (6) between the fan (2) and the part (3).Type: ApplicationFiled: December 20, 2019Publication date: February 24, 2022Applicant: SAFRAN AIRCRAFT ENGINESInventors: Paul Antoine FORESTO, Vivien Mickaël COURTIER, Stéphane Roger MAHIAS, William Henri Joseph RIERA
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Patent number: 11208198Abstract: A vane includes a fiber reinforcement having a three-dimensional weaving densified by a matrix, the fiber reinforcement including in a single woven part a root portion and an airfoil portion extending along a longitudinal direction between the root portion and a vane tip portion and along a transverse direction between a leading edge portion and a trailing edge portion. The airfoil portion includes first and second extrados and intrados faces. The fiber reinforcement includes a non-interlinking forming a housing inside the fiber reinforcement, a conformation part being present in the housing. The non-interlinking extends over a non-interlinked area inside the airfoil portion of the fiber reinforcement included between the root portion and the vane tip portion in the longitudinal direction and between the leading edge portion and the trailing edge portion in the transverse direction, the non-interlinking also opening outside the airfoil portion of the fiber reinforcement.Type: GrantFiled: January 15, 2020Date of Patent: December 28, 2021Assignee: SAFRAN AIRCRAFT ENGINESInventors: Vivien Mickaël Courtier, Dominique Gerhardt Mayhew, Adrien Jacques Philippe Fabre
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Patent number: 11174740Abstract: The invention relates to a vane (7) comprising: a structure made of composite material, a vane (7) root (16) attachment (9) comprising a base having a radial outer face (20) and in which a slot (24) configured to receive the vane (7) root (16) is formed and two platforms (26), extending on either side of the blade (18) opposite the radial outer face (20), and two stiffening parts (30), added and fixed on the radial outer face (20) on either side of the stilt (17) so as to tightly abut against the stilt (17).Type: GrantFiled: October 29, 2019Date of Patent: November 16, 2021Assignee: SAFRAN AIRCRAFT ENGINESInventors: Vivien Mickaël Courtier, Anthony Binder, Christophe Paul Jacquemard
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Patent number: 11155336Abstract: A reinforcing fiber structure for a propeller blade made of composite material is woven as a single piece to have an airfoil, a spar portion, and an enlarged portion. The fiber structure includes a zone of non-interlinking extending between the front and rear edges of the airfoil, and extending between an intermediate zone and the bottom edge of said airfoil. The spar portion extends inside the airfoil in the zone of non-interlinking, the spar portion extending outside the airfoil through the bottom edge of said airfoil. The enlarged portion extends from the spar portion outside the airfoil. The airfoil includes skins that are not interlinked with each other in the zone of non-interlinking and that surround the spar portion. The skins define two housings present inside the airfoil on respective sides of the spar portion and opening out through the bottom edge of the airfoil.Type: GrantFiled: January 11, 2019Date of Patent: October 26, 2021Assignee: SAFRAN AIRCRAFT ENGINESInventor: Vivien Mickaël Courtier
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Patent number: 11131197Abstract: A blade is provided including a structure made of composite material including a fibrous reinforcement obtained by three-dimensional weaving and a matrix in which the fibrous reinforcement is embedded, the structure made of composite material including an aerodynamically profiled blade portion and a blade root portion, the blade root portion including two sections each connected to the blade portion, a blade root fastening part including a wall delimiting a cavity and an opening formed in the wall, the structure made of composite material extending through the opening so that the blade portion is located outside the fastening part and the blade root portion is located inside the cavity, and a blocking part disposed in the cavity, between the two sections of the blade root portion, in order to keep the two sections apart from each other so as to oppose withdrawal of the blade root portion from the cavity via the opening.Type: GrantFiled: April 19, 2019Date of Patent: September 28, 2021Assignee: Safran Aircraft EnginesInventors: Vivien Mickael Courtier, Anthony Binder
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Patent number: 10794392Abstract: A hub for a propeller having variable-pitch blades for a turbomachine with longitudinal rotation axis, including a plurality of blade platforms, each one being designed to receive a blade root, the platforms being distributed around the annular outer periphery of the hub concentrically with the longitudinal rotation axis, wherein each blade platform has the general geometric shape of a spherical cap, and wherein, between two adjacent blade platforms around the longitudinal rotation axis, the transverse dimension, in particular the diameter, of the hub can vary axially and radially.Type: GrantFiled: February 20, 2017Date of Patent: October 6, 2020Assignee: SAFRAN AIRCRAFT ENGINESInventors: Paul Antoine Foresto, Vivien Mickaël Courtier, Christophe Paul Jacquemard
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Publication number: 20200300099Abstract: An aviation turbine engine having at least one unducted rotary propeller having a plurality of blades, each blade including: a blade body made of composite material including fiber reinforcement densified by a matrix, the fiber reinforcement of the blade body presenting three-dimensional weaving, the body extending between a leading edge and a trailing edge, and a protective fitting for protecting the leading edge and made of composite material having fiber reinforcement densified by a matrix, the fitting being adhesively bonded onto the leading edge of the blade body, the fitting being formed from a dry fiber preform injection molded with a densifying resin, and a polyurethane film for providing protection against erosion covering the blade body and the fitting.Type: ApplicationFiled: March 17, 2017Publication date: September 24, 2020Inventors: Adrien Jacques Philippe FABRE, Vivien Mickaël COURTIER, Adrien Louis Nicolas LAURENCEAU, Dominique Gerhadt MAYHEW
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Publication number: 20200223531Abstract: A vane includes a fiber reinforcement having a three-dimensional weaving densified by a matrix, the fiber reinforcement including in a single woven part a root portion and an airfoil portion extending along a longitudinal direction between the root portion and a vane tip portion and along a transverse direction between a leading edge portion and a trailing edge portion. The airfoil portion includes first and second extrados and intrados faces. The fiber reinforcement includes a non-interlinking forming a housing inside the fiber reinforcement, a conformation part being present in the housing. The non-interlinking extends over a non-interlinked area inside the airfoil portion of the fiber reinforcement included between the root portion and the vane tip portion in the longitudinal direction and between the leading edge portion and the trailing edge portion in the transverse direction, the non-interlinking also opening outside the airfoil portion of the fiber reinforcement.Type: ApplicationFiled: January 15, 2020Publication date: July 16, 2020Inventors: Vivien Mickaël COURTIER, Dominique Gerhardt MAYHEW, Adrien Jacques Philippe FABRE
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Publication number: 20200182073Abstract: The invention relates to a vane (7) comprising: a structure made of composite material, a vane (7) root (16) attachment (9) comprising a base having a radial outer face (20) and in which a slot (24) configured to receive the vane (7) root (16) is formed and two platforms (26), extending on either side of the blade (18) opposite the radial outer face (20), and two stiffening parts (30), added and fixed on the radial outer face (20) on either side of the stilt (17) so as to tightly abut against the stilt (17).Type: ApplicationFiled: October 29, 2019Publication date: June 11, 2020Applicant: SAFRAN AIRCRAFT ENGINESInventors: Vivien Mickaël COURTIER, Anthony BINDER, Christophe Paul JACQUEMARD
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Publication number: 20190323357Abstract: A blade is provided including a structure made of composite material comprising a fibrous reinforcement obtained by three-dimensional weaving and a matrix in which the fibrous reinforcement is embedded, the structure made of composite material comprising an aerodynamically profiled blade portion and a blade root portion, the blade root portion comprising two sections each connected to the blade portion, a blade root fastening part comprising a wall delimiting a cavity and an opening formed in the wall, the structure made of composite material extending through the opening so that the blade portion is located outside the fastening part and the blade root portion is located inside the cavity, and a blocking part disposed in the cavity, between the two sections of the blade root portion, in order to keep the two sections apart from each other so as to oppose withdrawal of the blade root portion from the cavity via the opening.Type: ApplicationFiled: April 19, 2019Publication date: October 24, 2019Applicant: Safran Aircraft EnginesInventors: Vivien Mickael COURTIER, Anthony BINDER
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Publication number: 20190217943Abstract: A reinforcing fiber structure for a propeller blade made of composite material is woven as a single piece to have an airfoil, a spar portion, and an enlarged portion. The fiber structure includes a zone of non-interlinking extending between the front and rear edges of the airfoil, and extending between an intermediate zone and the bottom edge of said airfoil. The spar portion extends inside the airfoil in the zone of non-interlinking, the spar portion extending outside the airfoil through the bottom edge of said airfoil. The enlarged portion extends from the spar portion outside the airfoil. The airfoil includes skins that are not interlinked with each other in the zone of non-interlinking and that surround the spar portion. The skins define two housings present inside the airfoil on respective sides of the spar portion and opening out through the bottom edge of the airfoil.Type: ApplicationFiled: January 11, 2019Publication date: July 18, 2019Inventor: Vivien Mickaël COURTIER
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Publication number: 20190048888Abstract: A hub for a propeller having variable-pitch blades for a turbomachine with longitudinal rotation axis, including a plurality of blade platforms, each one being designed to receive a blade root, the platforms being distributed around the annular outer periphery of the hub concentrically with the longitudinal rotation axis, wherein each blade platform has the general geometric shape of a spherical cap, and wherein, between two adjacent blade platforms around the longitudinal rotation axis, the transverse dimension, in particular the diameter, of the hub can vary axially and radially.Type: ApplicationFiled: February 20, 2017Publication date: February 14, 2019Applicant: Safran Aircraft EnginesInventors: Paul Antoine FORESTO, Vivien Mickaël COURTIER, Christophe Paul JACQUEMARD