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公开(公告)号：US11555406B2
公开(公告)日：2023-01-17
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：US12030615B2
公开(公告)日：2024-07-09
申请号：US18006089
申请日：2021-07-15
Applicant: SAFRAN AIRCRAFT ENGINES
Abstract: 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.
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公开(公告)号：US11959400B2
公开(公告)日：2024-04-16
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 , F01D5/3092 , F01D5/32 , 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：US20220143766A1
公开(公告)日：2022-05-12
申请号：US17427321
申请日：2020-02-04
Applicant: SAFRAN AIRCRAFT ENGINES
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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5.发明授权公开(公告)号：US12173725B2
公开(公告)日：2024-12-24
申请号：US18278999
申请日：2022-02-24
Applicant: Safran Aircraft Engines
Inventor： Vincent Joudon
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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Patent Agency Ranking
6.发明授权公开(公告)号：US11981418B2
公开(公告)日：2024-05-14
申请号：US18006285
申请日：2021-07-15
Applicant: SAFRAN AIRCRAFT ENGINES
CPC classification number: B64C11/06 , F04D29/323
Abstract: 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.
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公开(公告)号：US11821333B2
公开(公告)日：2023-11-21
申请号：US17625195
申请日：2020-07-09
Applicant: Safran Aircraft Engines
Inventor： Clément Pierre Postec , Vivien Mickaël Courtier , Vincent Joudon
CPC classification number: F01D5/14 , F01D5/282 , B29D99/0025 , F05D2220/36 , F05D2230/50
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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公开(公告)号：US12134460B2
公开(公告)日：2024-11-05
申请号：US17793877
申请日：2021-01-19
Applicant: Safran Aircraft Engines
Inventor： Vincent Joudon , Vivien Mickaël Courtier , Clément Pierre Postec
Abstract: 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).
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9.发明授权公开(公告)号：US12091986B2
公开(公告)日：2024-09-17
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：US12091156B2
公开(公告)日：2024-09-17
申请号：US18022385
申请日：2021-08-17
Applicant: SAFRAN AIRCRAFT ENGINES
Inventor： Vincent Joudon , Vivien Mickaël Courtier , Clément Pierre Postec
IPC: B64C11/26 , B29C70/48 , B29C70/50 , B64C11/02 , B64C11/04 , B64C11/06 , B64C11/16 , B64C11/20 , B64C27/26 , B64C27/467 , F03D1/00 , F03D1/06
CPC classification number: B64C11/26 , B29C70/48 , B64C11/06 , F03D1/0675 , B29C70/50 , B64C11/02 , B64C11/04 , B64C11/16 , B64C11/20 , B64C27/26 , B64C27/467 , F03D1/0658 , F03D1/101
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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