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公开(公告)号：US20210054743A1
公开(公告)日：2021-02-25
申请号：US16965845
申请日：2019-01-29
Applicant: Safran Aircraft Engines
Abstract: The invention relates to an assembly (1) for a turbine of a turbomachine, comprising: a first rotor disk (20a), a second rotor disk (20b), a part forming a mobile ring (28), comprising a system for preventing rotation of the mobile ring (28) relative to the rotor disks (20a, 20b), said system comprising: a rotor disk securing flange (222) having a plurality of teeth (224) that are distributed circumferentially about the turbomachine longitudinal axis (X-X), and a mobile ring securing flange (282) having a plurality of lugs (284) that are distributed circumferentially about the turbomachine longitudinal axis (X-X), the engagement of the rotor disk securing flange (222) with the mobile ring securing flange (282) ensuring, by means of the teeth (224) and the lugs (284), that the mobile ring (28) does not rotate relative to the rotor disks (20a, 20b).
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公开(公告)号：US20230125862A1
公开(公告)日：2023-04-27
申请号：US17906248
申请日：2021-03-19
Applicant: SAFRAN AIRCRAFT ENGINES
Abstract: A rotary assembly for a turbomachine including a rotor including at least two consecutive rotor stages provided with a plurality of blades and an annular rotor shroud connecting the two consecutive rotor stages, a stator including: at least one stator stage provided between the two consecutive rotor stages including a plurality of vanes, a turbomachine stator vane root, an annular clamping part and an annular support of abradable material, the root extending radially and being clamped axially between the annular support of abradable material and the annular clamping part, A space separates a radially internal end of the root and the annular support of abradable material. A turbojet engine including a rotary assembly as previously.
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公开(公告)号：US20230033362A1
公开(公告)日：2023-02-02
申请号：US17791829
申请日：2021-01-08
Applicant: SAFRAN AIRCRAFT ENGINES
Inventor： Antoine Hervé DOS SANTOS , Joao Antonio AMORIM , Pascal Grégory CASALIGGI , Nicolas Xavier TRAPPIER
Abstract: An assembly for a turbine engine turbine includes a turbine rotor disc centered on a longitudinal axis, a turbine shaft centered on the longitudinal axis and driven in rotation by the rotor disc. The assembly further includes first means of transmitting torque from the rotor disc to the shaft, wherein the rotor disc is locked in translation relative to the shaft in the direction of the longitudinal axis by a screwed member on the said shaft and second means of transmitting torque from the rotor disc to the screwed member. The screwed member has an unscrewing direction identical to the direction of rotation of the rotor disc in operation, and the second means of transmitting torque are configured to transmit the rotational torque from the rotor disc to the screwed member when the first means of transmitting torque cease to transmit torque from the rotor disc to the shaft.
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公开(公告)号：US20210189972A1
公开(公告)日：2021-06-24
申请号：US17055428
申请日：2019-05-15
Applicant: SAFRAN AIRCRAFT ENGINES
Inventor： Stéphane Pierre Guillaume BLANCHARD , Helene Myriam CONDAT , Nicolas Xavier TRAPPIER , Laurent Paul François PERROT
Abstract: The invention relates to a turbomachine comprising a low-pressure shaft (27) configured to drive a fan shaft (32) in rotation by means of a coupling assembly comprising a first shaft (1) on which are formed a plurality of first axial grooves (7), a second shaft (2) on which are formed a plurality of second axial grooves (12), and a coupling device (4) including a plurality of rolling elements (13) and an annular cage (14) positioned between the first shaft (1) and the second shaft (2), the rolling elements (13) being positioned between one of the first axial grooves (7) and one of the second axial grooves (12) to couple in rotation the first and the second shaft (1, 2), each first and second groove (7, 12) having a first (16) and a second (17) substantially planar surface inclined with respect to one another and extending along the axis.
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公开(公告)号：US20250043687A1
公开(公告)日：2025-02-06
申请号：US18720412
申请日：2022-12-14
Applicant: Safran Aircraft Engines
Inventor： Simon Jean-Marie Bernard COUSSEAU , Patrice Jean-Marc ROSSET , Nicolas Xavier TRAPPIER , Julian Nicolas GIRARDEAU , Patrick Joseph Marie GIRARD , Baptiste Dorian LAWNICZEK
Abstract: The present invention relates to a turbine rotor of a turbine engine of an aircraft, the rotor comprising a rotor disc provided at its periphery with a plurality of cavities for receiving the root of a blade. This rotor is characterised in that each blade comprises a circumferential coupling rib, in that it comprises a plurality of platforms, which comprise a main wall that is extended at its two ends by an upstream radial wall and by a downstream radial wall, the two longitudinal edges of each platform comprising a groove for receiving part of said coupling rib of one of the two blades between which this platform is assembled, and in that the height of each upstream radial wall is such that said wall extends radially inwards beyond the bottom of the cavity, until it is in front of the upstream face of the rotor disc.
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Patent Agency Ranking
公开(公告)号：US20220003127A1
公开(公告)日：2022-01-06
申请号：US17291503
申请日：2019-11-06
Applicant: SAFRAN AIRCRAFT ENGINES
Abstract: Assembly including a rotor disc, an adjacent stator and a plurality of sealing elements secured to the rotor disc, the stator including an inner platform and a root bearing at least one abradable element configured to cooperate with the sealing elements, the sealing elements being placed in an enclosure formed by the abradable element, the enclosure being open to the inside and delimited axially by an upstream abradable edge and a downstream abradable edge, the enclosure being delimited radially by an outer abradable edge, at least one of the sealing elements including a first lip configured to cooperate with the upstream abradable edge or the downstream abradable edge, and a second, separate lip configured to cooperate with the outer abradable edge.
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7.发明申请公开(公告)号：US20200277866A1
公开(公告)日：2020-09-03
申请号：US16738543
申请日：2020-01-09
Applicant: SAFRAN AIRCRAFT ENGINES
Abstract: The present invention relates to a rotor (1) of a turbomachine turbine, comprising a rotor disc (2) and a plurality of blades (3) distributed at its periphery, said rotor disc (2) comprising a plurality of mainly axial cells (23), each blade (3) comprising a root (32), retained in one of the cells (23) of said rotor disc, each root being dimensioned so as to form a space (4) between the bottom of the cell (23) and the radially inner face (324) of the root.This rotor is remarkable in that said root comprises a mainly axial blind hole (5) opening onto the upstream face of the root and a plurality of mainly radial air ejection orifices (6), each air ejection orifice (6) opening into said blind hole (5) and onto the radially inner face (324) of the root located facing the bottom of the cell (23).
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公开(公告)号：US20190153958A1
公开(公告)日：2019-05-23
申请号：US16076294
申请日：2017-02-08
Applicant: SAFRAN AIRCRAFT ENGINES
Inventor： Guillaume Patrice KUBIAK , Nils Edouard Romain BORDONI , Michel Gilbert Roland BRAULT , Romain Guillaume CUVILLIER , Benoit Jean Henri GOMANNE , Arnaud Nicolas NEGRI , Nicolas Xavier TRAPPIER
Abstract: The invention relates to a system for rotating a fan (2) of a turbojet engine (1) about a first rotation axis Ω, including a reduction gear (3) made up of a planetary gearset placed at the centre of the fan (2), which includes: a central sun gear (31); an outer planet gear (33) attached to the fan (2); at least one satellite gear (32) arranged between the central sun gear (31) and the outer planet gear (33) in order to transmit a rotary movement between the central sun gear (31) and the outer planet gear (33); characterised in that the outer planet gear (33) includes an inner portion (33a) which meshes with the satellite gear (32), as well as an outer portion (33b) to which blades (21) of the fan (2) are directly attached.
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公开(公告)号：US20180105278A1
公开(公告)日：2018-04-19
申请号：US15729504
申请日：2017-10-10
Applicant: SAFRAN AIRCRAFT ENGINES
Inventor： Nora EL GHANNAM , Matthieu Etienne ATTALI , Romain Jean-Claude FERRIER , Caroline Marie FRANTZ , Thomas Gerard Daniel RIVIERE , Nicolas Xavier TRAPPIER
CPC classification number: B64D27/26 , B64D27/12 , B64D29/08 , B64D2027/264 , F02C6/206 , F02C7/04 , F02C7/20 , F02C7/32 , F02C7/36 , F05D2220/323 , F05D2250/312 , F05D2260/15 , F05D2260/40 , F05D2260/4031 , Y02T50/671
Abstract: The invention relates to an aircraft propulsion assembly comprising a cradle receiving a turbine engine comprising at least one propeller having a longitudinal axis of rotation, a gas turbine engine having a longitudinal axis of rotation offset from the axis, and a reduction gear by means of which said propeller receives drive power from said engine, wherein the propeller and the gas turbine engine are designed such that axes and are offset from one another within said cradle at least by a given value in a transverse direction, the axis of the gas turbine engine being transversely closer to a proximal lateral side of the cradle than to an opposite distal lateral side of the cradle in order to create a lateral space between said engine and said distal lateral side of the cradle, thereby forming at least one region for installing equipments, components or accessories of said turbine engine.
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10.发明申请公开(公告)号：US20180066528A1
公开(公告)日：2018-03-08
申请号：US15698927
申请日：2017-09-08
Applicant: SAFRAN AIRCRAFT ENGINES
Inventor： Stéphane Pierre Guillaume BLANCHARD , Joao Antonio AMORIM , Maxime Aurélien ROTENBERG , Nicolas Xavier TRAPPIER
IPC: F01D5/30
Abstract: A turbine rotor is fitted to a turbomachine and includes disks each containing a coupling portion with recesses each holding a root of a blade, and coupled to one another by a first annular ferrule attached to one of them close to the recesses, and second rotationally coupled ferrules, which are respectively coupled radially to the disks, which each consists of at least two semi-annular sectors, and which form with the associated disk a space which communicates with the recesses of the coupling portion of this latter disk. In addition, each first ferrule includes through-holes enabling air to enter this space, and then the recesses, intended to cool the coupling portion which couples its disk and the blade roots.
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