公开(公告)号：US11795825B2

公开(公告)日：2023-10-24

申请号：US17622661

申请日：2020-06-22

Applicant: Safran Aircraft Engines

Inventor： Teddy Fixy ,  Jérémy Guivarc'h ,  Gilles Pierre-Marie Notarianni ,  Thomas Alain De Gaillard

IPC: F01D5/14

CPC classification number: F01D5/147 ,  F05D2220/32 ,  F05D2240/30

Abstract: The invention relates to an inter-blade platform of a turbomachine fan, comprising: —a base comprising a first surface configured to delimit a flow path in the fan and a second surface on the opposite side from the first surface, —two flanks extending radially next to the second surface, each of the flanks having a sacrificial free end configured to bear against a fan disc.

公开(公告)号：US11015462B2

公开(公告)日：2021-05-25

申请号：US16418147

申请日：2019-05-21

Applicant: SAFRAN AIRCRAFT ENGINES

Inventor： Thomas Alain De Gaillard ,  Clément Pierre Postec ,  Charles-Henri Claude Jacky Sullet

IPC: F01D5/28 ,  F04D29/02 ,  F04D29/38

Abstract: A blade body made of composite material includes fiber reinforcement densified by a matrix, the blade body extending in a longitudinal direction between a root or bottom portion and a tip or top portion, and in a transverse direction between a leading edge and a trailing edge. The fiber reinforcement of the blade body includes a first portion constituted by a plurality of yarn layers interlinked by three-dimensional or multilayer weaving, and a second portion forming all or part of at least one leading edge or at least one trailing edge of a blade. The second portion includes a plurality of short fibers oriented in random manner, the yarns of the plurality of yarn layers of the first portion and the short fibers of the second portion being embedded in the matrix.

公开(公告)号：US10519776B2

公开(公告)日：2019-12-31

申请号：US15569665

申请日：2016-04-26

Applicant: Safran Aircraft Engines

Inventor： Caroline Jacqueline Denise Berdou ,  Thomas Alain De Gaillard

IPC: F01D5/14 ,  F01D5/28 ,  B29B11/06 ,  B29C45/02 ,  B29C45/14 ,  B29K63/00 ,  B29K105/20 ,  B29L31/08

Abstract: A preform for a turbine engine blade, the preform comprising a main fiber preform obtained by three-dimensional weaving and comprising a first longitudinal segment suitable for forming a blade root (21), a second longitudinal segment extending the first longitudinal segment upwards, and suitable for forming an airfoil portion (22), and a first transverse segment extending transversely from the junction between the first and second longitudinal segments, and suitable for forming a first platform (23), wherein the preform also includes at least one stiffener (40) fitted on the main fiber preform along at least a portion of the distal edge of the first transverse segment.

公开(公告)号：US11982209B2

公开(公告)日：2024-05-14

申请号：US18010751

申请日：2021-06-09

Applicant: SAFRAN AIRCRAFT ENGINES

Inventor： Clément Pierre Postec ,  Thomas Alain De Gaillard ,  Teddy Fixy ,  Eddy Keomorakott Souryavongsa

IPC: F01D5/28 ,  B29C70/22 ,  B29C70/34 ,  B29C70/86 ,  B29K307/04 ,  B29K705/00 ,  B29L31/08 ,  F01D5/00 ,  F01D5/14

CPC classification number: F01D5/282 ,  B29C70/222 ,  B29C70/34 ,  B29C70/86 ,  F01D5/005 ,  F01D5/147 ,  B29K2307/04 ,  B29K2705/00 ,  B29L2031/082 ,  F05D2220/32 ,  F05D2230/23 ,  F05D2230/80 ,  F05D2240/30

Abstract: A blade for an aircraft gas turbine engine includes, in a longitudinal direction, a blade root, a shank and an aerofoil body, the aerofoil body extending in the longitudinal direction between the shank and a blade tip and in a transverse direction between a leading edge made of metal material and a trailing edge. The blade includes a blade core made of composite material having a three-dimensional woven fibrous reinforcement forming the blade root, the shank and a part of the aerofoil body. The blade also includes a skin made of composite material having a two-dimensional woven fibrous reinforcement surrounding the aerofoil body part of the blade core, the skin being interposed between the leading edge made of metal material and a front edge of the aerofoil body part of the blade core to define a thinned leading edge portion, the skin including one or more two-dimensional woven plies.

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：US11313239B2

公开(公告)日：2022-04-26

申请号：US17057550

申请日：2019-05-20

Applicant: SAFRAN AIRCRAFT ENGINES

Inventor： Thomas Alain De Gaillard ,  Alexandre Bernard Marie Boisson ,  Rémi Roland Robert Mercier ,  Alexis Thomas Chaboud

IPC: F01D5/30 ,  F04D29/32 ,  F04D29/34 ,  F01D5/32

Abstract: A disc able to support platforms and blades of a fan, and including an external surface having a succession of grooves for receiving the fan blades and teeth interposed between the grooves to support the fan platforms, an upstream face of the disc, and a plurality of radial protrusions disposed radially around the axis of the disc on the upstream face of the disc, and able to be fastened to a fan platform retaining flange, the protrusions being offset radially toward the interior of the disc relative to the grooves of the disc, and being disposed circumferentially between two teeth of the disc.

公开(公告)号：US11021973B2

公开(公告)日：2021-06-01

申请号：US16086492

申请日：2017-03-20

Applicant: SAFRAN AIRCRAFT ENGINES

Inventor： Thomas Alain De Gaillard ,  Alexandre Bernard Marie Boisson

IPC: F01D5/30 ,  F01D11/00

Abstract: A platform suitable for being interposed between two adjacent blades of a fan, and including a passage wall, a bottom wall, and axial and radial retention surfaces. The passage wall defines a fan air flow passage, the bottom wall presents a main surface for bearing against a fan disk, and the axial and radial retention surfaces are arranged at the two axial ends of the platform. The radial retention surface arranged at the upstream axial end of the platform is radially offset from the main surface of the bottom wall in the direction in which the bottom wall bears against the disk.

公开(公告)号：US11686203B2

公开(公告)日：2023-06-27

申请号：US17905267

申请日：2021-02-19

Applicant: SAFRAN AIRCRAFT ENGINES

Inventor： Frédéric Jean-Bernard Pouzadoux ,  Jérémy Guivarc'h ,  Thomas Alain De Gaillard

IPC: F01D5/14 ,  F01D5/28

CPC classification number: F01D5/147 ,  F01D5/282 ,  F05D2220/323 ,  F05D2240/24 ,  F05D2240/30 ,  F05D2300/6012 ,  F05D2300/6034

Abstract: The invention relates to a fibrous texture intended to form the fibrous reinforcement of a turbine engine blade made of composite material, the texture being in a single piece and having a three-dimensional weave between a plurality of first fiber warp yarns or strands extending in a radial direction and a plurality of first fiber weft yarns or strands extending in a chord direction, the texture comprising a blade root portion and a blade airfoil portion extending between the blade root portion and a free end of the fibrous texture. The blade airfoil portion has a reinforced area in the vicinity of the free end of the texture comprising weft yarns or strands made of second fibers different from the first fibers.

公开(公告)号：US10570757B2

公开(公告)日：2020-02-25

申请号：US15787838

申请日：2017-10-19

Applicant: Safran Aircraft Engines

Inventor： Thomas Alain De Gaillard ,  Alexandre Bernard Marie Boisson ,  Gilles Pierre-Marie Notarianni ,  Charles-Henri Claude Jacky Sullet

IPC: F01D5/32 ,  F01D5/30 ,  F01D5/02 ,  F01D5/12

Abstract: A turbomachine rotary assembly includes a plurality of blades having roots positioned in the grooves of a rotor disk and an axial retention system of the blades. The axial retention system includes a removable lock mounted bearing against the upstream axial ends of two consecutive teeth of the disk so as to block the opening of the groove formed by the teeth. It includes removable parts suitable for being mounted at the upstream axial ends of the teeth and to block the lock by clamping the lock between the removable parts and the teeth once the lock is installed against the upstream axial ends of the teeth.

公开(公告)号：US10233939B2

公开(公告)日：2019-03-19

申请号：US15205265

申请日：2016-07-08

Applicant: SAFRAN AIRCRAFT ENGINES

Inventor： Thomas Alain De Gaillard ,  Alexandre Bernard Marie Boisson ,  Audrey Laguerre

IPC: F04D29/34 ,  F04D19/00 ,  F04D29/64 ,  F04D29/02 ,  F02K3/06 ,  F01D11/00 ,  F01D5/30 ,  F01D5/32

Abstract: A fan assembly for an aviation turbine engine, the assembly including a fan disk having at least one tooth and at least one platform mounted on the tooth of the fan disk, the platform including a box of composite material made from fiber reinforcement densified by a matrix, the box having a flow passage wall, a bottom wall, and two side walls extending radially between the bottom wall and the flow passage wall. The box of the platform includes an upstream opening at an upstream end of the platform and a downstream opening, and the assembly also includes a locking key housed in the box and passing through the upstream and downstream openings of the box, the locking key being blocked at each of its ends by a blocking element.