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1.发明公开公开(公告)号：US20240141917A1
公开(公告)日：2024-05-02
申请号：US18278999
申请日：2022-02-24
Applicant: Safran Aircraft Engines
Inventor： Vincent JOUDON
CPC classification number: F04D29/388 , B29C70/24 , B29C70/443 , F04D29/023 , B29L2031/082
Abstract: 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.
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公开(公告)号：US20230286644A1
公开(公告)日：2023-09-14
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 , F01D7/00 , F01D5/30 , B64C11/06 , 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：US20210293152A1
公开(公告)日：2021-09-23
申请号：US17262528
申请日：2019-07-24
Applicant: Safran Aircraft Engines
Inventor： Vincent JOUDON , Franck Bernard Léon VARIN
Abstract: 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.
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公开(公告)号：US20240286733A1
公开(公告)日：2024-08-29
申请号：US18656993
申请日：2024-05-07
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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公开(公告)号：US20240229655A9
公开(公告)日：2024-07-11
申请号：US17769617
申请日：2020-10-16
Applicant: SAFRAN AIRCRAFT ENGINES
Inventor： Vivien Mickaël COURTIER , Christophe Paul JACQUEMARD , Vincent JOUDON
CPC classification number: F01D5/3007 , B64C11/06 , F01D5/326 , F01D7/00 , F05D2220/36
Abstract: 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).
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Patent Agency Ranking
6.发明公开公开(公告)号：US20240175363A1
公开(公告)日：2024-05-30
申请号：US18285122
申请日：2022-03-24
Applicant: Safran Aircraft Engines
CPC classification number: F01D5/147 , F01D5/141 , F01D5/282 , F05D2220/36
Abstract: The present invention relates to a vane (7) of a turbine engine, comprising: —a structure which has an aerodynamic profile (20); —a spar (21) comprising a vane root portion (24), a blade portion (25) arranged inside the structure which has an aerodynamic profile (20), and a stilt portion (26), the blade portion (25) comprising a body (27) connected to the vane root portion (24) and two arms extending radially from the body (27); and —a structural reinforcement (31) extending from the vane root portion (24) to the body (27) of the blade portion (25), the structural reinforcement (31) being rigidly connected to the vane root portion (24) and configured to form a force path separate from the stilt portion (26) in the event of failure of the spar (21) within the stilt portion (26).
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公开(公告)号：US20230286649A1
公开(公告)日：2023-09-14
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 (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.
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公开(公告)号：US20230286643A1
公开(公告)日：2023-09-14
申请号：US18006130
申请日：2021-07-15
Applicant: SAFRAN AIRCRAFT ENGINES
IPC: B64C11/06
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：US20230141180A1
公开(公告)日：2023-05-11
申请号：US17802830
申请日：2021-02-26
Applicant: Safran Aircraft Engines
Inventor： Vincent JOUDON , Régis Eugène Henri SERVANT
CPC classification number: F01D7/00 , F01D5/3007 , F01D5/32 , F01D5/3092 , F05D2260/74
Abstract: 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). This rotor is characterised in that an elongated wedge (2) and a prestressing rod (3) with at least one cam (33) are also arranged in each cell (17), the bottom of the cell (17) comprising as many retraction cavities (173) as the rod (3) comprises cams (33), in that the prestressing rod (3) is interposed between the wedge (2) and the bottom (171) of the cell (17), so that said cam (33) is facing a corresponding retraction cavity (173) and in that the prestressing rod (3) can rotate about its longitudinal axis (X2-X′2), between a rest position, in which the cam (33) is housed in the retraction cavity (173), and an armed position, in which the cam (33) exerts a radial pressure on the central region (22) of the wedge (2) so as to move the wedge (2) towards the blade root (150).
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公开(公告)号：US20220268159A1
公开(公告)日：2022-08-25
申请号：US17625195
申请日：2020-07-09
Applicant: Safran Aircraft Engines
Inventor： Clément Pierre POSTEC , Vivien Mickaël COURTIER , Vincent JOUDON
Abstract: 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.
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