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1.发明公开公开(公告)号：US20240263560A1
公开(公告)日：2024-08-08
申请号：US18699150
申请日：2022-09-30
Applicant: SAFRAN AIRCRAFT ENGINES , SAFRAN CERAMICS
Inventor： Patrick Joseph Marie GIRARD , Didier René André ESCURE , Matthieu Arnaud GIMAT , Sébastien Serge Francis CONGRATEL , Arthur DE CASTRO
CPC classification number: F01D5/3084 , F01D5/141 , F01D9/041 , F05D2300/6033
Abstract: Blade of a turbomachine turbine including a airfoil extending along a first direction between an internal end and an external end, a base secured to said internal end, and a root secured to said external end and extending, along a second direction perpendicular to said first direction, between an upstream edge, and a downstream edge and, along a third direction orthogonal to the first and second directions, between first and second lateral edges, the first side edge having, in a plane including the second and third directions, a shape complementary to that of the second lateral edge. The first lateral edge includes a first portion extending from the upstream edge, and a second portion externally protruding along the third direction at an acute angle with the first portion.
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公开(公告)号：US20220260012A1
公开(公告)日：2022-08-18
申请号：US17626637
申请日：2020-07-08
Applicant: SAFRAN AIRCRAFT ENGINES
Inventor： Didier René André ESCURE , Nicolas Jérôme Jean TANTOT
Abstract: A combustion chamber of an aircraft turbomachine having a main axis includes: a body of revolution coaxial with the main axis having a plurality of combustion tubes extending mainly in the direction of the main axis and being distributed in a ring about the main axis; a first perforated rotary disc mounted at a first axial end of the body and rotatable about the main axis to selectively open or close a first end of each of the combustion tubes; and a second perforated rotary disc mounted at a second axial end of the body and rotatable about the main axis to selectively open or close a second end of each of the combustion tubes. The body includes a plurality of cooling segments extending mainly in the direction of the main axis, which are distributed in a ring about the main axis and around the combustion tubes.
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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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