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公开(公告)号：US20210164362A1
公开(公告)日：2021-06-03
申请号：US17045229
申请日：2019-03-28
Applicant: SAFRAN AIRCRAFT ENGINES
Inventor： Simon Nicolas MORLIERE , Julian Nicolas GIRARDEAU , Sébastien Jean Laurent PRESTEL , Ghislain Hervé ABADIE , Benjamin Franklin François GILLOT
IPC: F01D25/14
Abstract: Cooling device (21) extending circumferentially around a turbomachine casing, such as a turbine casing, comprising a support (24) extending axially and designed to be secured to the casing, at least one cooling tube extending circumferentially, at least one securing member (25), comprising a radially inner portion (36) at least partially surrounding the tube, and a radially outer portion (37) secured to the support (24), the radially outer portion (37) of the securing member (25) being secured to the support (24) via the intermediary of a connection member (30) comprising a central portion (31) having a circumferential end portion (32) and a second circumferential end portion (32) which are circumferentially opposite, the first end portion (32) and the second end portion (32) each extending in an opposite axial direction, the first and second end portions (32, 32) each being secured to the support (24), the radially outer portion (37) of the securing member (25) being secured to the central portion (31) of the connection member (30).
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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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Patent Agency Ranking
3.发明申请公开(公告)号：US20230120507A1
公开(公告)日：2023-04-20
申请号：US17760340
申请日：2021-02-15
Applicant: SAFRAN AIRCRAFT ENGINES
Inventor： Julian Nicolas GIRARDEAU
Abstract: A turbine includes a rotor surrounded by a stator, a first movable stage including a series of rotating vanes, a second movable stage including a second series of rotating vanes, a distributor including a series of stationary vanes, the vanes including platforms jointly delimiting a separation between a main space in which a hot flow circulates through the vanes, and a secondary space surrounding a hub of the rotor. The rotor includes an aperture through which air is blown towards the secondary space, this air being discharged towards the main space. Straightening fins are carried by the distributor in the secondary space for straightening the air flow in order to change its gyration.
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4.发明申请公开(公告)号：US20220275731A1
公开(公告)日：2022-09-01
申请号：US17632475
申请日：2020-07-31
Applicant: SAFRAN AIRCRAFT ENGINES
Inventor： Julian Nicolas GIRARDEAU
IPC: F01D11/12
Abstract: An abradable member for a turbomachine turbine, including a cellular structure including walls defining wells which open through a wear face. The cellular structure includes at least one flow straightener jutting from the wear face.
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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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公开(公告)号：US20240117750A1
公开(公告)日：2024-04-11
申请号：US18271893
申请日：2022-01-18
Applicant: SAFRAN AIRCRAFT ENGINES
Inventor： Julian Nicolas GIRARDEAU , Benoit Guillaume SILET
CPC classification number: F01D11/122 , F01D5/20 , F05D2250/11 , F05D2250/12
Abstract: A rotor of a turbine extending around a longitudinal axis includes a rotor disc bearing at its periphery one or more rotor blades, each blade including an airfoil provided at its radially outer end with a platform equipped with an upstream lip and a downstream lip, the platform having a front lateral edge and a back lateral edge with respect to the normal direction of rotation of the rotor about the longitudinal axis, and a suction face portion which extends from the front lateral edge to the suction face of the airfoil. The upstream lip and the downstream lip each includes sawtooth-shaped cut-outs such as to form a front tooth and a back tooth which are contiguous, in that the back tooth has a cutting edge and in that the front tooth of each lip is disposed on the suction face portion of the platform.
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公开(公告)号：US20210164361A1
公开(公告)日：2021-06-03
申请号：US17046724
申请日：2019-03-28
Applicant: SAFRAN AIRCRAFT ENGINES
Inventor： Simon Nicolas MORLIERE , Julian Nicolas GIRARDEAU , Sébastien Jean Laurent PRESTEL , Ghislain Hervé ABADIE , Benjamin Franklin François GILLOT
IPC: F01D25/12
Abstract: The invention relates to a cooling device (21) extending circumferentially around a turbine engine casing (1), such as, for example, a turbine casing (7), comprising a support (24) extending axially and intended to be attached to the casing (18), at least one cooling tube (23) extending circumferentially, at least one attachment member (25) comprising a radially inner portion (36) at least partially surrounding the tube (23), and a radially outer portion (37) attached to the support (24), the radially outer portion (37) of the attachment member (25) being attached to the support (24) through connecting means (30) formed by L-shaped sheets.
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