Safran Aircraft Engines

Thomas Alain De Gaillard

Alexandre Bernard Marie Boisson

Guillaume Pascal Jean-Charles Gondre

Gilles Pierre-Marie Notarianni

Jérémy Guivarc'h

Teddy Fixy

Caroline Jacqueline Denise Berdou

Audrey Myriam Laguerre

Matthieu Arnaud Gimat

Clément Pierre Postec

Eddy Keomorakott Souryavongsa

Claire Marie Figeureu

Pierre Jean Faivre D'arcier

Charles-Henri Claude Jacky Sullet

Paula Salas De Los Rios

Alexandre Bernard Boisson

Caroline Jacqueline Berdou

William Henri Joseph Riera

Benjamin Bulot

Frédéric Jean-Bernard Pouzadoux

Rémi Roland Robert Mercier

Guillaume Olivier Vartan Martin

Sébastien Marin

Alexis Thomas Chaboud

Pierre-Antoine Gérard Joseph Barbier

Oscar-Emmanuel Gnangnon

Sebastien Marin

Audrey Laguerre

The present invention relates to a fan blade of a turbomachine comprising a structure made of composite material comprising a fibrous reinforcement obtained by three-dimensional weaving of strands and a matrix in which the fibrous reinforcement is embedded, which comprises a first portion forming the suction-side wall and a second portion forming the pressure-side wall, the strands of the fibrous reinforcement comprising first strands comprising carbon or aramid fibres, the Young's modulus of which is greater than 250 GPa, and second strands produced from a viscoelastic material and having a Young's modulus less than 10 GPa, the first portion comprises uniquely first strands whereas the second portion comprises second strands.

Hybridization of the fibers of the fibrous reinforcement of a fan blade with elastic fibers

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.

Vane made of composite material having a three-dimensional woven fibrous reinforcement and two-dimensional woven skin and method for manufacturing same

The present invention relates to a turbomachine rotary-fan blade (), comprising a body () made of a composite material, a metal reinforcement part () comprising a metal upstream nose (), characterised in that the metal upstream nose () comprises, at least on the metal part () of the blade tip, a recess () of longitudinally tapering thickness (AX), delimiting on the metal part () over a height (H) at least one metal projection () with prescribed wear, which has a longitudinally tapering thickness and which is configured to detach at least partially in the presence of tangential friction in the second thickness direction (EP) against the metal part (), the recess () and the metal projection () with prescribed wear extending the first metal fin () and/or the second metal fin () and/or the upstream edge () of the body () made of composite material.

Turbomachine rotary-fan blade, fan and turbomachine provided therewith

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.

Turbomachine rotary fan blade, fan, and turbomachine provided therewith

The invention relates to a blade of a fan of a turbomachine, comprising a structure made from composite material, including a fibrous reinforcement obtained by means of the three-dimensional weaving of strands and a matrix in which the fibrous reinforcement is embedded,&#x2014;the fibrous reinforcement comprising a first portion forming the leading edge and a second portion forming all or part of the trailing edge,&#x2014;the strands of the fibrous reinforcement comprising first strands having a predetermined elongation at break and second strands having an elongation at break higher than that of the first strands, the first portion comprising all or some of the first strands while the second portion comprises all or some of the second strands.

Hybridization of the fibers of the fibrous reinforcement of a fan blade

The invention relates to an inter-blade platform of a turbomachine fan, comprising: &#x2014;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, &#x2014;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.

Inter-blade platform with a sacrificial box section

The present invention relates to a fan blade () having a structure made from a composite material, comprising a fibrous reinforcement (), which is obtained by three-dimensional weaving of warp strands and weft strands, and a matrix in which the fibrous reinforcement () is embedded, wherein&#x2014;the fibrous reinforcement () comprises a first portion () forming the trailing edge () of the structure made from a composite material and a second portion () forming its leading edge (), and wherein&#x2014;the warp strands of the fibrous reinforcement () comprise first strands () having a predetermined stiffness and second strands () having a greater stiffness than that of the first strands (), the first portion () comprising all or part of the first strands () and being devoid of second strands () while the second portion () comprises all or part of the second strands ().

Fan blade comprising an insert of stiff fibers

A preform for a turbine engine blade, comprising a main fiber preform obtained by three-dimensional weaving and comprising: a first longitudinal segment, suitable for forming a blade root; a second longitudinal segment, extending upwards from the first longitudinal segment and suitable for forming an airfoil portion; and a first transverse segment, extending transversely from the junction between the first and second longitudinal segments to a substantially linear distal edge and suitable for forming a first platform; the preform further including at least one attachment tab provided under the first transverse segment at its distal edge, suitable for forming an attachment portion of the platform.

Blade provided with platforms possessing attachment portions

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.

Fibrous texture for turbine engine blade made of composite material

The invention relates to a fan blade () comprising: &#x2014;an aerofoil () made of a composite material comprising a fibrous reinforcement densified by a polymer matrix, a leading edge () and a trailing edge (), and &#x2014;a structural shield () fitted and attached to the leading edge () or the training edge (), and &#x2014;at least one stiffener () formed integrally and in one piece with the structural shield (), said stiffener () extending in a cavity () formed between the shield () and the leading edge () or the trailing edge () so as to increase a stiffness of the blade ().

Fan blade comprising a thin shield and a stiffener

The invention relates to a blade of a fan of a turbomachine, comprising a structure made from composite material, including a fibrous reinforcement Obtained by means of the three-dimensional weaving of strands and a matrix in which the fibrous reinforcement is embedded. According to the invention, the fibrous reinforcement comprises a first portion forming the leading edge and a second portion forming all or part of the trailing edge, and the strands of the fibrous reinforcement comprise first strands having a predetermined elongation at break and second strands having an elongation at break higher than that of the first strands, the first portion comprising all or some of the first strands while the second portion comprises all or some of the second strands.

Hybridization of fibers of the fibrous reinforcement of a fan blade

A sealing arrangement is provided between inner and outer coaxial ring-shaped walls of an aircraft engine. The outer wall has an axial end with a U-shaped cross-section parallel to axis, the opening therein being oriented axially in a first direction. The inner wall has an axial end with a U-shaped cross-section parallel to axis, the opening therein being oriented axially in the opposite direction. The U-shaped end of the outer wall includes a ring-shaped free edge axially engaged in the opening in the axial end of the inner wall. The U-shaped end of the inner wall includes a ring-shaped free edge axially engaged in the opening in the axial end of the outer wall. The walls define therebetween a ring-shaped gas channel having a substantially S-shaped axial cross-section.

Sealing arrangement between two ring-shaped walls of an aircraft engine

The invention concerns a fan blade for a turbomachine, comprising: a leading edge and a pressure-side wall, a structural shield, said shield being attached and fixed to the leading edge of the blade and comprising a pressure-side fin attached to the pressure-side wall, and a piece of fabric comprising aramid fibres, attached and fixed to the pressure-side wall of the fan blade such that the piece of fabric extends in the continuation of the pressure-side fin of the shield without covering said pressure-side fin.

Fabric comprising aramid fibres for protecting a blade against impacts

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.

Turbmachine fan disc

A fibrous texture to form the fibrous reinforcement of a turbomachine blade made of composite material, the texture being made in one piece and having a three-dimensional weaving, and includes blade root, blade airfoil and blade support portions. The blade support portion includes a first area extending transversely from a first edge of the texture to form a leading edge and a second area extending transversely from the first area up to a second edge of the texture to form a trailing edge, the first area including warp yarns or strands made of second fibers different from the first fibers, the second fibers having an elongation at break greater than that of the first fibers, the first area having a first volume ratio in yarns or strands made of second fibers strictly greater than a second volume ratio in yarns or strands made of second fibers in the second area.

Growing community of inventors

Moissy-Cramayel, France

Thomas Alain De Gaillard