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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
摘要： 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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2.发明授权公开(公告)号：US12025030B2
公开(公告)日：2024-07-02
申请号：US17910514
申请日：2021-03-11
CPC分类号： F01D5/282 , B29D99/0025 , B64D27/10 , F01D5/32
摘要： The present invention relates to a blade comprising: —a structure made of composite material; —a blade root attachment part comprising a wall delimiting a cavity, a first opening formed in the wall and a second opening located under the blade root portion, the structure made of composite material extending through the first opening; —two locking parts configured to axially abut against a shoulder of the attachment part and to bear against the blade root portion; and —a cover for compressing the blade root portion against the locking parts.
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公开(公告)号：US11473430B2
公开(公告)日：2022-10-18
申请号：US17416897
申请日：2019-12-20
发明人： Paul Antoine Foresto , Vivien Mickaël Courtier , Stéphane Roger Mahias , William Henri Joseph Riera
摘要： 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).
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4.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
CPC分类号： F01D5/147 , F01D5/141 , F01D5/282 , F05D2220/36
摘要： 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
IPC分类号： 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分类号： 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
摘要： 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：US12071863B2
公开(公告)日：2024-08-27
申请号：US17753591
申请日：2020-09-02
发明人： Vivien Mickaël Courtier , Dominique Gerhardt Mayhew , Adrien Jacques Philippe Fabre , Adrien Louis Nicolas Laurenceau
IPC分类号： F01D5/28 , B29C70/02 , B29C70/68 , F01D5/14 , B29K105/08 , B29K105/16 , B29L31/08
CPC分类号： F01D5/282 , B29C70/025 , B29C70/682 , F01D5/147 , B29K2105/0845 , B29K2105/16 , B29K2995/0097 , B29L2031/082 , F05D2220/36 , F05D2300/6012 , F05D2300/603 , F05D2300/612
摘要： 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.
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公开(公告)号：US11174740B2
公开(公告)日：2021-11-16
申请号：US16667150
申请日：2019-10-29
摘要： 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).
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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
CPC分类号： B64C11/06 , F01D7/00 , F04D29/323 , F04D29/644 , F05D2260/70
摘要： 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：US11873076B2
公开(公告)日：2024-01-16
申请号：US18006128
申请日：2021-07-15
发明人： Clément Cottet , Vivien Mickaël Courtier , Vincent Joudon , Arnaud Langlois , Régis Eugène Henri Servant , Laurent Jablonski
CPC分类号： B64C11/30 , B64C11/06 , F01D5/30 , F01D7/00 , F05D2260/70
摘要： 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
CPC分类号： B64C11/06 , F04D29/323
摘要： 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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