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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：US20240209745A1
公开(公告)日：2024-06-27
申请号：US18541080
申请日：2023-12-15
Applicant: SAFRAN AIRCRAFT ENGINES
CPC classification number: F01D5/3007 , F01D5/143 , F05D2220/323 , F05D2240/307
Abstract: A blade includes a root to be mounted in a slot of plural slots which opens out at an outer periphery of a rotor disk of a movable wheel of a low-pressure turbine of an aeronautical propulsion system, the rotor disk being centered on a longitudinal axis and the slots being circumferentially distributed about the longitudinal axis, the rotor disk further including blades circumferentially distributed at the outer periphery of the rotor disk, each blade being mounted in a corresponding slot, the root including a first platform which has a radially outer surface, a shroud having a second platform which has a radially inner surface, and an airfoil extending from the root to the shroud, the airfoil having a leading edge and a trailing edge. The shroud is formed of a material and has a defined difficulty.
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公开(公告)号：US20240200509A1
公开(公告)日：2024-06-20
申请号：US18541252
申请日：2023-12-15
Applicant: SAFRAN AIRCRAFT ENGINES
IPC: F02K3/06
CPC classification number: F02K3/06 , F05D2220/323 , F05D2220/36 , F05D2230/51
Abstract: A propulsion system includes a drive shaft, a drive turbine including a drive turbine rotor having a turbine disk and turbine blades, and a fan section. The turbine disk has an inner surface, an outer surface, a bore radius, and a rim radius. One or more of the turbine blades includes a root fixed to the turbine disk in a respective slot, a stilt connected to the root and including a platform, and an airfoil connected to the platform and extending within a flowpath. The flowpath includes an outer radius and an inner radius. The drive shaft has a limit speed. The bore radius, the rim radius, the outer radius, the inner radius, and the limit speed satisfy a given relationship.
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公开(公告)号：US20240209776A1
公开(公告)日：2024-06-27
申请号：US18541234
申请日：2023-12-15
Applicant: SAFRAN AIRCRAFT ENGINES
CPC classification number: F01D5/30 , B64C11/001 , B64C11/04 , B64C11/20 , F01D25/00 , F05D2230/60
Abstract: The present disclosure relates to an aeronautical propulsion system (1) comprising:
a drive shaft (11);
a drive turbine (8); and
a fan section (2).
Figure for the abstract: FIG. 2-
公开(公告)号：US20240209743A1
公开(公告)日：2024-06-27
申请号：US18541042
申请日：2023-12-15
Applicant: SAFRAN AIRCRAFT ENGINES
CPC classification number: F01D5/3007 , B64C11/04 , B64C11/20 , F01D15/00
Abstract: A blade includes a root to be mounted in a slot of plural slots which open out at an outer periphery of a rotor disk of a movable wheel of a low-pressure turbine of an aeronautical propulsion system, the rotor disk being centered on a longitudinal axis and the slots being circumferentially distributed about the longitudinal axis, the rotor disk having an upstream surface and a downstream surface, each slot being delimited by a bottom surface, the rotor disk including blades circumferentially distributed at the outer periphery of the rotor disk, each blade being mounted in a corresponding slot, the root including a first platform which has a radially outer surface; a shroud having a second platform which has a radially inner surface; and an airfoil extending from the root to the shroud, the airfoil having a leading edge and a trailing edge.
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公开(公告)号：US20240200499A1
公开(公告)日：2024-06-20
申请号：US18541066
申请日：2023-12-15
Applicant: SAFRAN AIRCRAFT ENGINES
CPC classification number: F02C7/36 , F01D5/06 , F01D5/14 , F05D2220/323
Abstract: A propulsion system includes a drive shaft, a drive turbine including a drive turbine stator and a drive turbine rotor, the rotor being connected to the drive shaft and including a turbine disk and turbine blades, and a fan section including a fan rotor and a fan stator, the drive shaft being connected to the fan rotor. The turbine disk has an inner surface, an outer surface delimiting slots distributed about a longitudinal axis, one or more of the turbine blades including a root fixed to the turbine disk in a respective slot. A bore width of the inner surface, and a rim radius of the outer surface of the turbine disk, and a limit speed of the drive shaft are defined in relation to each other.
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