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公开(公告)号：US11731221B2
公开(公告)日：2023-08-22
申请号：US17427321
申请日：2020-02-04
Applicant: SAFRAN AIRCRAFT ENGINES
CPC classification number: B23P19/04 , B23P6/002 , B24C1/10 , B24C5/005 , B26F3/06 , B64C11/205 , F01D5/005 , F01D5/288 , F05D2230/10
Abstract: 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.
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公开(公告)号：US11199094B2
公开(公告)日：2021-12-14
申请号：US16520489
申请日：2019-07-24
Applicant: SAFRAN AIRCRAFT ENGINES
Inventor： Vincent Joudon , Franck Bernard Léon Varin
Abstract: A turbine machine blade has an aerodynamic surface that is made of organic matrix composite material reinforced by fibers and metal structural reinforcement that is adhesively bonded by an epoxy adhesive bond on the leading edge, which is of matching shape, and that presents along its entire height a section that is substantially V-shaped with a base extended by two lateral flanks of respective profiles that become thinner at free ends going towards the trailing edge. In order to increase the toughness of the epoxy adhesive bond in the event of the epoxy adhesive bond cracking, the epoxy adhesive bond includes a reinforcing sheet of elastomeric polymer enabling the reinforcing sheet to be torn into two portions, the elastomeric polymer having the following properties at 23° C.: Young's modulus E≈10 MPa; stress at rupture σr>10 MPa; strain at rupture εr>80%.
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公开(公告)号：US12140046B2
公开(公告)日：2024-11-12
申请号：US18032048
申请日：2020-10-16
Applicant: Safran Aircraft Engines
Inventor： Vivien Mickaël Courtier , Christophe Paul Jacquemard , Vincent Joudon
Abstract: The invention relates to an assembly for a turbine engine blade, the assembly comprising a fastener defining a well for receiving a blade root, and a clamping device for clamping the blade root against the fastener when the blade root is received in the well, wherein the clamping device comprises: at least one clamping member suitable for bearing simultaneously on the blade root and on the fastener in the well so as to exert a clamping force on the blade root, the clamping member defining a threaded hole, and a resilient layer arranged to bear in the well on the blade root, a rod comprising a thread engaging with the threaded hole so that a rotation of the rod with respect to the clamping member causes a variation in the clamping force exerted by the clamping member on the root.
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公开(公告)号：US12012201B2
公开(公告)日：2024-06-18
申请号：US18006106
申请日：2021-07-15
Applicant: SAFRAN AIRCRAFT ENGINES
CPC classification number: B64C11/06 , F01D7/00 , F04D29/323 , F04D29/644 , F05D2260/70
Abstract: 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.
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Patent Agency Ranking
公开(公告)号：US11993365B2
公开(公告)日：2024-05-28
申请号：US18006344
申请日：2021-07-15
Applicant: SAFRAN AIRCRAFT ENGINES
Inventor： Clement Cottet , Vivien Mickael Courtier , Vincent Joudon , Regis Eugene Henri Servant , Laurent Jablonski
Abstract: 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 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.
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公开(公告)号：US11873076B2
公开(公告)日：2024-01-16
申请号：US18006128
申请日：2021-07-15
Applicant: SAFRAN AIRCRAFT ENGINES
Inventor： Clément Cottet , Vivien Mickaël Courtier , Vincent Joudon , Arnaud Langlois , Régis Eugène Henri Servant , Laurent Jablonski
CPC classification number: B64C11/30 , B64C11/06 , F01D5/30 , F01D7/00 , F05D2260/70
Abstract: 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.
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公开(公告)号：US11851157B2
公开(公告)日：2023-12-26
申请号：US18006130
申请日：2021-07-15
Applicant: SAFRAN AIRCRAFT ENGINES
CPC classification number: B64C11/06 , F04D29/323
Abstract: 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.
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公开(公告)号：US20230348042A1
公开(公告)日：2023-11-02
申请号：US18022385
申请日：2021-08-17
Applicant: SAFRAN AIRCRAFT ENGINES
Inventor： Vincent Joudon , Vivien Mickaël Courtier , Clément Pierre Postec
CPC classification number: B64C11/26 , B29C70/48 , F03D1/0675 , B64C11/06
Abstract: 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.
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公开(公告)号：US10794818B2
公开(公告)日：2020-10-06
申请号：US16114479
申请日：2018-08-28
Applicant: SAFRAN AIRCRAFT ENGINES
Inventor： Vincent Joudon , Pierre Antoine Bossan , Matthew Savage
IPC: G01N19/04
Abstract: A peel testing device designed to test the resistance to peeling of test pieces each formed from a support and from a reinforcement glued to this support, and comprising a frame with a face roller and at least one guide roller, a traction machine configured to peel the reinforcement from the surface of the support in a peeling direction tangential to the face roller and a sensor for measuring the force exerted by the traction machine during peeling, the device also comprising a fastening cable connected, on the one hand, to the traction machine and on the other hand to the face roller with which it forms a pulley system and the face roller which has a greater diameter than that of the guide roller comprises a mounting element for holding the reinforcement fixedly there.
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