Patents by Inventor Vincent JOUDON
Vincent JOUDON 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: 20240141917Abstract: The present invention relates to a blade comprising: a structure of aerodynamic profile comprising two mutually opposite skins; and a spar comprising a fibrous reinforcement obtained by three-dimensional weaving and densified by the matrix, the spar comprising a blade root portion extending outside the structure of aerodynamic profile and an airfoil portion arranged inside the structure of aerodynamic profile between the two skins. Moreover, within the blade root portion, the fibrous reinforcement of the spar comprises a non-debound region and at least two debound regions extending radially from the non-debound region so as to form at least four separate branches.Type: ApplicationFiled: February 24, 2022Publication date: May 2, 2024Applicant: Safran Aircraft EnginesInventor: Vincent JOUDON
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Publication number: 20240133300Abstract: Assembly for a turbomachine blade, comprising: a fastener (9) defining a pocket (10) for receiving a blade root (11), and comprising two flanks defining between them a passage leading into the pocket (10) and forming stops preventing the root (11) from exiting from the pocket (10) via the passage, a shim (26a, 26b) adapted to be received in the pocket (10) with the root (11), the shim (26a, 26b) having a first support surface (28a, 28b) to bear on the root (11) and a second support surface (30a, 30b) opposite the first support surface (28a, 28b) to bear against the fastener (9), the support surfaces being fixed relative to each other and oriented such that movement of the shim (26a, 26b) in the pocket (10) relative to the fastener (9) varies the value of force exerted by the shim (26a, 26b) on the root (11).Type: ApplicationFiled: October 15, 2020Publication date: April 25, 2024Applicant: SAFRAN AIRCRAFT ENGINESInventors: Vivien Mickaël COURTIER, Christophe Paul JACQUEMARD, Vincent JOUDON
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Patent number: 11959400Abstract: The present invention relates to a fan rotor with variable pitch blades, comprising a rotor disc, equipped at its periphery with a plurality of rotary fasteners (16), each fastener (16) comprising a cell (17) for receiving the root (150) of a blade (15).Type: GrantFiled: February 26, 2021Date of Patent: April 16, 2024Assignee: SAFRAN AIRCRAFT ENGINESInventors: Vincent Joudon, Régis Eugène Henri Servant
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Patent number: 11873076Abstract: An assembly including a propeller blade and a pitch adjustment system for setting the pitch of the blade. A root of the blade has a bulb and the pitch adjustment system for setting the pitch of the blade includes a cup having an upper opening; —a retaining ring, which extends around the bulb, is restricted at least in terms of axial movement towards the opening relative to the cup and has a bearing face to inhibit axial movement of the root towards the opening The pitch adjustment system being further includes a lower seat for the root to engage the cup, the seat and/or the retaining ring being mounted so as to be capable of axial translation relative to the cup by at least one clamping mechanism.Type: GrantFiled: July 15, 2021Date of Patent: January 16, 2024Assignee: SAFRAN AIRCRAFT ENGINESInventors: Clément Cottet, Vivien Mickaël Courtier, Vincent Joudon, Arnaud Langlois, Régis Eugène Henri Servant, Laurent Jablonski
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Patent number: 11851157Abstract: A system for controlling the pitch of a propeller blade for an aircraft turbine engine, including a cup having an annular wall extending about an axis intended to be a pitch setting axis of the blade, and a bottom wall configured so as to cooperate in a form-fitting manner with a free end of the root so that the cup is prevented from rotating relative to the root about the axis, and a locking ring that is configured so as to be mounted within the cup and to cooperate respectively with the root and the annular wall of the cup in order to ensure axial retention of the root in the cup.Type: GrantFiled: July 15, 2021Date of Patent: December 26, 2023Assignee: SAFRAN AIRCRAFT ENGINESInventors: Vincent Joudon, Clément Cottet, Vivien Mickaël Courtier, Régis Eugène Henri Servant
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Publication number: 20230383658Abstract: The invention relates to an assembly for a turbine engine blade, the assembly comprising a fastener (9) defining a well (10) for receiving a blade root (7), and a clamping device (32) for clamping the blade root (7) against the fastener (9) when the blade root (7) is received in the well (10), wherein the clamping device (32) comprises: at least one clamping member (34; 36) suitable for bearing simultaneously on the blade root (7) and on the fastener (9) in the well (10) so as to exert a clamping force on the blade root (7), the clamping member (34; 36) defining a threaded hole, and a resilient layer (44) arranged to bear in the well on the blade root, a rod (38) comprising a thread engaging with the threaded hole so that a rotation of the rod (38) with respect to the clamping member causes a variation in the clamping force exerted by the clamping member on the root.Type: ApplicationFiled: October 16, 2020Publication date: November 30, 2023Applicant: Safran Aircraft EnginesInventors: Vivien Mickaël COURTIER, Christophe Paul JACQUEMARD, Vincent JOUDON
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Patent number: 11821333Abstract: 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: GrantFiled: July 9, 2020Date of Patent: November 21, 2023Assignee: SAFRAN AIRCRAFT ENGINESInventors: Clément Pierre Postec, Vivien Mickaël Courtier, Vincent Joudon
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Publication number: 20230348042Abstract: An unducted fan having variable pitch blades for an aircraft or wind propulsion system is described. The fan includes a hub provided with housings pivotally receiving vanes about radial axes, and an outer casing of the hub into which circular openings of the housings open. Each vane includes a root which is rotatably mounted in the associated housing, a radially oriented blade and a disc-shaped platform extending from the blade to an edge of the circular opening. The blade includes at least one skin which includes a free lower edge facing the side of the root, wherein the platform is attached to the free lower edge of the skin.Type: ApplicationFiled: August 17, 2021Publication date: November 2, 2023Applicant: SAFRAN AIRCRAFT ENGINESInventors: Vincent Joudon, Vivien Mickaël Courtier, Clément Pierre Postec
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Publication number: 20230339600Abstract: A system for controlling the pitch of a propeller blade for an aircraft turbine engine is provided. The system generally includes a cup having an annular wall extending about a pitch setting axis of the blade, the annular wall having a lower axial end enclosed by a bottom wall, and an upper axial end that is open and configured so as to enable a root of the blade to be mounted in the cup; and a locking ring that extends around the pitch setting axis and is configured to be mounted around the root, the locking ring being a double dog ring that comprises two annular rows of outer dogs constituting active and safety dogs, respectively.Type: ApplicationFiled: July 15, 2021Publication date: October 26, 2023Inventors: Clément COTTET, Vivien Mickaël COURTIER, Vincent JOUDON, Régis Eugène Henri SERVANT
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Publication number: 20230294817Abstract: Disclosed is a variable pitch propeller blade for an aircraft turbine engine. The blade includes an airfoil connected to a root, the root having a body housed in an annular barrel that extends around a pitch axis of the blade, the body including a free end opposite the airfoil; a shoulder towards the airfoil; and a bulb located between the free end and the shoulder. The bulb can have a cross-section, referred to as the middle section, that has a maximum value Sm, and the barrel can be affixed to the body and covers and matches at least a portion of the bulb and the shoulder.Type: ApplicationFiled: July 15, 2021Publication date: September 21, 2023Applicant: SAFRAN AIRCRAFT ENGINESInventors: Vincent JOUDON, Clément COTTET, Vivien Mickaël COURTIER, Laurent JABLONSKI, Régis Eugène Henri SERVANT
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Publication number: 20230294816Abstract: An assembly for an aircraft turbine engine is provided. The assembly generally includes an un-ducted propeller blade of which the root has a bulbous portion; a system for setting the pitch of the blade about a pitch setting axis, the pitch setting system including a cup, configured to be placed inside the outer casing, has a flared open top end for axial insertion of the root and in which the root of the blade can be axially affixed by a locking member; and at least one radial retention prong in a radial space reserved between the wall of the cup and the root.Type: ApplicationFiled: July 15, 2021Publication date: September 21, 2023Inventors: Clément COTTET, Vivien Mickaël COURTIER, Vincent JOUDON, Thierry Georges Paul PAPIN
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Publication number: 20230286649Abstract: An assembly comprising a propeller blade and its system for angularly adjusting the pitch of the blade including a bowl which is radially delimited by an annular wall (44)-extending about an axis for adjusting the pitch of the blade, the bowl having a bottom wall, a free lower end of the root being fitted axially into a complementary housing of the bottom wall in order to rotatably connect the bowl and the blade about the pitch-adjustment axis. The root of the blade comprises a first limiting face that engages with a first abutment face of the bowl to limit the rotation of the blade in the event of breakage of the lower end of the root.Type: ApplicationFiled: July 15, 2021Publication date: September 14, 2023Inventors: Clement COTTET, Vivien Mickael COURTIER, Vincent JOUDON, Regis Eugene Henri SERVANT, Laurent JABLONSKI
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Publication number: 20230286643Abstract: A system for controlling the pitch of a propeller blade for an aircraft turbine engine, including a cup having an annular wall extending about an axis intended to be a pitch setting axis of the blade, and a bottom wall configured so as to cooperate in a form-fitting manner with a free end of the root so that the cup is prevented from rotating relative to the root about the axis, and a locking ring that is configured so as to be mounted within the cup and to cooperate respectively with the root and the annular wall of the cup in order to ensure axial retention of the root in the cup.Type: ApplicationFiled: July 15, 2021Publication date: September 14, 2023Inventors: Vincent JOUDON, Clément COTTET, Vivien Mickaël COURTIER, Régis Eugène Henri SERVANT
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Publication number: 20230286644Abstract: An assembly including a propeller blade and a pitch adjustment system for setting the pitch of the blade. A root of the blade has a bulb and the pitch adjustment system for setting the pitch of the blade includes a cup having an upper opening; a retaining ring, which extends around the bulb, is restricted at least in terms of axial movement towards the opening relative to the cup and has a bearing face to inhibit axial movement of the root towards the opening The pitch adjustment system being further includes a lower seat for the root to engage the cup, the seat and/or the retaining ring being mounted so as to be capable of axial translation relative to the cup by at least one clamping mechanism.Type: ApplicationFiled: July 15, 2021Publication date: September 14, 2023Inventors: Clément COTTET, Vivien Mickaël COURTIER, Vincent JOUDON, Arnaud LANGLOIS, Régis Eugène Henri SERVANT, Laurent JABLONSKI
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Patent number: 11731221Abstract: A method for separating a first mechanical part from a second mechanical part is described, wherein the second mechanical part is bonded to the first mechanical part by an adhesive film along a connecting area, the first mechanical part having a first specific thermal conductivity and the second mechanical part having a second thermal conductivity that is higher than the first thermal conductivity. The method includes at least one cooling step during which the second mechanical part is cooled to a negative temperature and at least one stressing step during which the second mechanical part is subjected to mechanical stress in order to cause the adhesive film to break.Type: GrantFiled: February 4, 2020Date of Patent: August 22, 2023Assignee: SAFRAN AIRCRAFT ENGINESInventors: Vincent Joudon, Damien Bruno Lamouche, Matthieu Patrick Jean Roger Perlin
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Publication number: 20230257105Abstract: A system for controlling the pitch setting of a propeller blade for an aircraft turbine engine is provided. The system generally including a blade having an airfoil connected to a root; a cup having an annular wall extending about a pitch axis of the blade and a lower axial end enclosed by a bottom wall; a locking ring that extends around the root and inside the cup; a safety element that ensures the retention of the root relative to the cup. The at least one safety element can have a generally elongate shape and can pass through aligned holes in the bottom wall of the cup and in the free end of the root.Type: ApplicationFiled: July 15, 2021Publication date: August 17, 2023Inventors: Clément COTTET, Vivien Mickaël COURTIER, Vincent JOUDON, Régis Eugène Henri SERVANT
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Publication number: 20230141180Abstract: The present invention relates to a fan rotor with variable pitch blades, comprising a rotor disc, equipped at its periphery with a plurality of rotary fasteners (16), each fastener (16) comprising a cell (17) for receiving the root (150) of a blade (15).Type: ApplicationFiled: February 26, 2021Publication date: May 11, 2023Applicant: Safran Aircraft EnginesInventors: Vincent JOUDON, Régis Eugène Henri SERVANT
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Publication number: 20230044779Abstract: The present invention relates to a blade (7) comprising: —a composite material structure (17), —a blade root fastening portion (9) further comprising a shoulder (10) extending into the recess from the wall—a base (18) arranged in the recess and comprising a support member configured to abut against the shoulder (10) of the blade root fastening portion (9) and a passage (39) formed in the support member, the sections (23) of the blade root portion (22) of the composite material structure extending through the passage (39), and—a blocking part (19) arranged in the recess between the two sections (23) of the blade root portion (22) such that each section of the blade root portion (23) is pressed against the support member by the blocking part (19).Type: ApplicationFiled: January 19, 2021Publication date: February 9, 2023Applicant: Safran Aircraft EnginesInventors: Vincent JOUDON, Vivien Mickaël COURTIER, Clément Pierre POSTEC
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Patent number: 11555406Abstract: A turbine engine blade having an aerodynamic surface extending a first direction between a leading edge and a trailing edge and in a second direction, perpendicular to the first direction, between a root of the blade and a tip of the blade, the aerodynamic surface being made of a fiber-reinforced organic matrix composite material, and a metallic structural reinforcement bonded by an adhesive joint to the leading edge whose shape it follows and which has over its entire height a substantially V-shaped section with a base extended by two lateral flanks having a thinned profile at free ends directed toward the trailing edge, the adhesive joint being locally supplemented below the free ends of the lateral flanks by an elastomeric polymer introduced in the form of solid particles into the adhesive joint and adhered to the aerodynamic surface and/or the free ends of the lateral flanks during a polymerization phase.Type: GrantFiled: July 24, 2019Date of Patent: January 17, 2023Assignee: Safran Aircraft EnginesInventors: Vincent Joudon, Franck Bernard Léon Varin
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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