公开(公告)号：US12060811B2

公开(公告)日：2024-08-13

申请号：US17441619

申请日：2020-03-19

Applicant: SAFRAN ,  SAFRAN AIRCRAFT ENGINES

Inventor： Jeremy Philippe Pierre Edynak ,  Jeremy Guivarc'h ,  Lola Auliac ,  Thibaut Dominique Augustin Girard ,  Pierre Jean Faivre D'Arcier

IPC: F01D11/00 ,  F01D5/30

CPC classification number: F01D5/3007 ,  F01D11/003 ,  F05D2220/32 ,  F05D2230/60 ,  F05D2240/30 ,  F05D2240/55

Abstract: The invention relates to a fan rotor for a turbomachine, including a fan disk, fan blades with a leading edge and a trailing edge, platforms inserted between the blades and fixed to the periphery of the disk, each including an aerodynamic surface extending from the leading edges to the trailing edges of the blades. The aerodynamic surface includes an upstream longitudinal portion on the side of the leading edges and a downstream longitudinal portion on the side of the trailing edges, the upstream longitudinal portion being supported by a first member of the platform fixed to the disk in a pivotable manner, and the downstream longitudinal portion being independent of the upstream longitudinal portion and supported by a second member of the platform which is independent of the first member and fixed to the disk in a pivotable manner.

公开(公告)号：US11078918B2

公开(公告)日：2021-08-03

申请号：US16733620

申请日：2020-01-03

Applicant: SAFRAN AIRCRAFT ENGINES ,  SAFRAN

Inventor： Thibaut Dominique Augustin Girard ,  Lola Auliac ,  Jérémy Guivarc'h ,  Jérémy Philippe Pierre Edynak ,  Pierre Jean Faivre D'Arcier

IPC: F04D29/08 ,  F01D5/02 ,  F01D11/00

Abstract: Seal (10) for an inter-blade platform intended to extend circumferentially about an axis and to be mounted between two axial ends of the inter-blade platform, including a first part (10a) in contact with a first blade adjacent to a first circumferential end of the platform, and a second part (10b) in contact with a second blade adjacent to a second circumferential end of the platform, the first part (10a) and the second part (10b) of the seal (10) being fixed to each other such that a displacement in the circumferential direction of one of the two parts (10a, 10b) of the seal (10) causes a displacement of the other part (10a, 10b) of the seal (10) in the same direction, when the two parts (10a, 10b) of the seal (10) are fixed to each other.

公开(公告)号：US11885239B2

公开(公告)日：2024-01-30

申请号：US17776103

申请日：2020-11-18

Applicant: SAFRAN AIRCRAFT ENGINES

Inventor： Guillaume Pascal Jean-Charles Gondre ,  Thomas Alain De Gaillard ,  Pierre Jean Faivre D'Arcier

IPC: F01D5/28 ,  F01D5/14

CPC classification number: F01D5/282 ,  F01D5/147 ,  F05D2300/6034

Abstract: The invention relates to a turbomachine rotary-fan blade having a predetermined breaking zone, which extends from the upstream edge along a given length and from the blade-tip edge over a given height. According to the invention, the body is made of a composite material comprising a fibre reinforcement obtained by three-dimensional weaving of warp and weft strands, and a resin matrix in which the fibre reinforcement is embedded, and has, in or in the vicinity of the zone, a discontinuity of at least some of the strands, configured such that the zone partially detaches when there is tangential friction in the thickness direction against the blade-tip edge, the height being less than 3% of the aerodynamic stream height of the blade.

公开(公告)号：US11111798B2

公开(公告)日：2021-09-07

申请号：US16490115

申请日：2018-03-01

Applicant: SAFRAN

Inventor： Nicolas Pierre Lanfant ,  Pierre Jean Faivre D'Arcier

IPC: F01D5/28 ,  F01D9/04 ,  F01D5/14 ,  B29D99/00 ,  B29L31/08 ,  D03D25/00

Abstract: A blade of a turbomachine includes a blade body of composite material having a fiber reinforcement having a three-dimensional weave and densified by a matrix, the reinforcement having a first part extended by a second, end, part including two segments separated from each other; and an insert having a pi-shaped section, the insert having a platform part and two longitudinal flanges separated from each other, the platform part including a housing delimited by a bottom wall and a rim, the bottom wall including an opening communicating with the space between the two flanges, the first part of the fiber reinforcement being clamped between the two flanges of the insert, the segments of the second part of the fiber reinforcement being folded against the bottom wall of the housing.

公开(公告)号：US12006840B2

公开(公告)日：2024-06-11

申请号：US18021128

申请日：2021-08-09

Applicant: Safran

Inventor： Matteo Minervino ,  Pierre Jean Faivre D'Arcier ,  Damien Bruno Lamouche ,  Tony Alain Roger Joël Lhommeau

IPC: F01D5/28 ,  B29C45/14 ,  B29D99/00 ,  F01D5/02 ,  B29K63/00 ,  B29K105/08 ,  B29K223/00 ,  B29K267/00 ,  B29K277/00 ,  B29K307/04 ,  B29K309/08 ,  B29L31/08

CPC classification number: F01D5/282 ,  B29C45/14819 ,  B29D99/0025 ,  F01D5/021 ,  B29K2063/00 ,  B29K2105/0845 ,  B29K2223/06 ,  B29K2267/00 ,  B29K2277/10 ,  B29K2307/04 ,  B29K2309/08 ,  B29L2031/08 ,  F05D2220/36 ,  F05D2230/23 ,  F05D2300/603

Abstract: Blower vane for an aircraft turbine engine, the vane comprising a blade connected to a root, the vane being made of a woven fibre-based composite material embedded in a polymeric resin, the vane further comprising a medium for identifying the vane, which is a radio-identification medium, the blower vane being characterised in that it comprises at least a first portion the fibres of which are only electrically conductive fibres, and at least a second portion the fibres of which are formed by a mixture of electrically conductive fibres and non-electrically conductive fibres, and in that the identification medium is located in or on the second portion.

公开(公告)号：US20240026792A1

公开(公告)日：2024-01-25

申请号：US18021128

申请日：2021-08-09

Applicant: Safran

Inventor： Matteo Minervino ,  Pierre Jean Faivre D'Arcier ,  Damien Bruno Lamouche ,  Tony Alain Roger Joël Lhommeau

IPC: F01D5/28 ,  F01D5/02 ,  B29D99/00 ,  B29C45/14

CPC classification number: F01D5/282 ,  F01D5/021 ,  B29D99/0025 ,  B29C45/14819 ,  F05D2220/36 ,  F05D2300/603 ,  F05D2230/23 ,  B29L2031/08

Abstract: Blower vane for an aircraft turbine engine, the vane comprising a blade connected to a root, the vane being made of a woven fibre-based composite material embedded in a polymeric resin, the vane further comprising a medium for identifying the vane, which is a radio-identification medium, the blower vane being characterised in that it comprises at least a first portion the fibres of which are only electrically conductive fibres, and at least a second portion the fibres of which are formed by a mixture of electrically conductive fibres and non-electrically conductive fibres, and in that the identification medium is located in or on the second portion.