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1.发明公开公开(公告)号：US20240102397A1
公开(公告)日：2024-03-28
申请号：US18256339
申请日：2021-12-03
Applicant: SAFRAN AIRCRAFT ENGINES
CPC classification number: F01D11/001 , F01D9/041 , F01D11/005 , F05D2240/56
Abstract: A turbine stator assembly including a guide vane assembly and a sealing ring bearing an abradable element of a dynamic sealing ring. The assembly includes pins secured to the sealing ring and cooperating with respective oblong openings formed in the guide vane assembly so as to allow a radial movement of the ring with respect to the guide vane assembly in order to compensate for differential thermal expansions. A seal is arranged so as to compensate for circumferential spaces between ring sectors forming the guide vane assembly.
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公开(公告)号：US20220162951A1
公开(公告)日：2022-05-26
申请号：US17593793
申请日：2020-04-03
Applicant: Safran Aircraft Engines
Inventor： Patrick Jean Laurent SULTANA , Clément Charles Jérémy COIFFIER , Olivier RENON , Laurent Cédric ZAMAI
Abstract: Counter-rotating turbine (C) of a turbomachine (10) extending about an axis (X) and comprising an inner rotor configured to rotate about the axis of rotation (X), and comprising an inner drum on which an inner movable blading (22) is fixed, an outer rotor configured to rotate about the axis of rotation (X) in a direction opposite to the inner rotor, and comprising an outer drum (50) on which an outer movable blading (20) is fixed, the outer movable blading (20) comprising at least one fixing rod (212) extending through an orifice (51) of the outer drum (50), the outer movable blading (20) being fixed to the outer drum (50) via a clamping means (100) fixed to the fixing rod (212) from an outer face of the outer drum (50), a set ring (80) being disposed around the fixing rod (50) in the orifice (51) of the outer drum (50).
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公开(公告)号：US20250003348A1
公开(公告)日：2025-01-02
申请号：US18701033
申请日：2022-10-14
Applicant: Safran Aircraft Engines
Abstract: The present invention relates to a nozzle guide vane for a turbine, having an axis of revolution and comprising: a flange extending radially relative to the axis; —a ring seal mounted on the flange and comprising an inner face that is configured to bear an abradable element; —a ventilation cavity delimited radially on the inside by an outer face of the ring seal and downstream by an upstream face of the flange; —a baffle configured to guide an airflow toward the ventilation cavity; and—at least one through-opening formed in the ring seal and configured to put the ventilation cavity in fluidic communication with the inner face of the ring seal.
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公开(公告)号：US20210108526A1
公开(公告)日：2021-04-15
申请号：US16496368
申请日：2018-03-23
Applicant: SAFRAN AIRCRAFT ENGINES
Abstract: The invention relates to a turbomachine assembly comprising: —a casing comprising: —an internal hub (10), —an external ferrule (20) extending around and at a distance from the internal hub (10), —a hollow arm (30), provided with a longitudinal cavity (40) and connecting the internal hub (10) and the external ferrule (20), —a tube (50) configured to extend in the interior of the longitudinal cavity (40) of the hollow arm (30) of the casing and comprising a central support (60) comprising two elastic blades (61) and configured to exert a pressure on the wall (42) of the longitudinal cavity (40) when the tube (50) is extended in the interior of the longitudinal cavity (40); characterized in that the material(s) of the elastic blades (61) is (are) such that said elastic blades (61) have a stress curve between the minimum and maximum stress curves of table A.
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公开(公告)号：US20240337201A1
公开(公告)日：2024-10-10
申请号：US18580890
申请日：2022-07-20
Applicant: SAFRAN AIRCRAFT ENGINES
Inventor： Vianney SIMON , Patrice Jean-Marc ROSSET , Patrick Jean Laurent SULTANA , Jean-Claude Christian TAILLANT
CPC classification number: F01D25/183 , F02C7/36 , F05D2260/31
Abstract: The present invention relates to a rotating assembly of a turbomachine, comprising:—a shaft configured to drive a propeller of the turbo machine around an axis and comprising a first flange radially extending from the shaft, the first flange being monolithic with the shaft;—a sleeve fitted onto the shaft and comprising a second flange radially extending from the sleeve, the sleeve being attached to the first flange of the shaft by means of the second flange; and—at least one component connected to the shaft by means of the sleeve so as to be rigidly connected to the shaft to move therewith, the component comprising at least one sealing element.
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Patent Agency Ranking
公开(公告)号：US20240093638A1
公开(公告)日：2024-03-21
申请号：US17754858
申请日：2020-10-08
Applicant: SAFRAN AIRCRAFT ENGINES
Inventor： Simon Jean-Marie Bernard COUSSEAU , Mathieu Patrick Henri DELALANDRE , Patrick Jean Laurent SULTANA , Laurent Cédric ZAMAI
IPC: F02C3/067
CPC classification number: F02C3/067 , F05D2240/24 , F05D2250/44
Abstract: A counter-rotating turbine for a turbine engine comprising an inner rotor having an inner drum to which is attached a plurality of inner impellers rotatably supported by a first shaft, an outer rotor comprising an outer drum to which is fastened a plurality of outer impellers rotatably supported by a second shaft coaxial with the first shaft, the outer rotor comprising a downstream impeller having a plurality of downstream moving blades extending between an outer shroud and an inner shroud, one upstream end of the outer shroud being attached downstream of said outer drum, the inner shroud being attached to the second shaft, at least one of the inner shroud and of the outer shroud comprising at least one flexible transition part configured to allow elastic deformation of said shroud in the radial direction.
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公开(公告)号：US20220389874A1
公开(公告)日：2022-12-08
申请号：US17763095
申请日：2020-09-21
Applicant: SAFRAN AIRCRAFT ENGINES
Inventor： Patrick Jean Laurent SULTANA , Stéphane Pierre Guillaume BLANCHARD , Antoine Hervé DOS SANTOS
Abstract: The invention relates to an assembly for a turbine engine, comprising a radially inner shaft (3) and a radially outer shaft (7), said shafts (7, 8) being coaxial and extending along an axis (X), means (11, 15) for coupling said inner and outer shafts (7, 8) in rotation, means (22) for axially holding the inner shaft (8) relative to the outer shaft (7), means for centring the inner shaft (8) relative to the outer shaft (7), characterised in that the centring means comprise a shim (14) for radial centring and for axial positioning, this shim being frustoconical and interposed between a frustoconical centring surface (13) of the inner shaft (8) and a corresponding frustoconical centring surface (10) of the outer shaft (7).
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8.发明申请公开(公告)号：US20250035003A1
公开(公告)日：2025-01-30
申请号：US18837511
申请日：2023-02-07
Applicant: Safran Aircraft Engines
Inventor： Patrick Jean Laurent SULTANA , Matthieu SIMON , Loic ANSART , Joao Antonio AMORIM
Abstract: The present invention relates to a turbine rotor (1) comprising a rotor disc (2), provided at its periphery with a plurality of axial cells (23) for receiving a bilobed root (30) of a blade (3), each cell (23) comprising a radially inner cavity (232) and a radially outer cavity (231). This rotor is characterised in that it comprises a ring (4) for axially retaining the blade roots and an annular flange (5), the ring (4) comprising a radially inner portion provided with notches (43) and being arranged against the upstream face (21) of the disc (2), so that each of its notches (43) is located opposite a cell (23) of the disc (2), the flange (5) being secured against the upstream face of the ring (4), forming a space (E) with said disc (2), and comprising at least one air-intake opening (54) which opens into said space (E), and in that each blade (3) comprises a groove (33) for receiving the outer circumferential edge (46) of said ring (4).
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公开(公告)号：US20220186633A1
公开(公告)日：2022-06-16
申请号：US17440073
申请日：2020-03-16
Applicant: SAFRAN AIRCRAFT ENGINES
Abstract: A counter-rotating turbine of an aircraft turbomachine, includes a casing including an endoscopy port configured for an endoscopy plug of a non-destructive testing device to pass into the casing. The endoscopy plug includes a mechanism for acquiring and transmitting images. The non-destructive testing device includes a mechanism for receiving and displaying images connected to the mechanism for acquiring and transmitting images by a wireless connection. First and second rotors are configured to rotate in opposite rotation directions, the second rotor having an endoscopy port in which the endoscopy plug is removably attached.
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10.发明申请公开(公告)号：US20210355830A1
公开(公告)日：2021-11-18
申请号：US17266653
申请日：2019-08-26
Applicant: SAFRAN AIRCRAFT ENGINES
Inventor： Patrick Jean Laurent SULTANA , Arnaud Lasantha GENILIER
Abstract: A rotor disc for a turbomachine, the disc extending circumferentially about an axis and including a plurality of cavities configured to receive blade roots, each cavity including a downstream radial wall configured to axially block the blade root in the cavity, each downstream radial wall including a channel of ventilation of the cavity, including an inlet orifice which opens into the cavity and an outlet orifice which opens onto a downstream surface of the disc. An assembly for a turbomachine including such a disc and an upstream retention ring and a turbomachine including such an assembly.
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