Safran Aircraft Engines

Safran

Jérémy Guivarc'h

Thomas Alain De Gaillard

Matthieu Arnaud Gimat

François Charleux

Dominique Raulin

Thibault Ruf

Gilles Pierre-Marie Notarianni

Frédéric Jean-Bernard Pouzadoux

Alain Jacques Michel Bassot

Jean-Louis Romero

Alexandre Bernard Marie Boisson

Teddy Fixy

Pierre Jean Faivre D'arcier

Jérémy Philippe Pierre Edynak

Paula Salas De Los Rios

Pierre Faivre D'Arcier

Jean-Noël Mahieu

Thibaut Dominique Augustin Girard

Lola Auliac

Gérald Diogo

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 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 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 leading-edge shield for a turbomachine blade includes a pressure-side wing and a suction-side wing. Both the pressure-side wing and suction-side wing extend heightwise from a bottom edge to a top edge and lengthwise from the leading edge to a respective rear edge. They are connected together via the leading edge. The rear edge of the suction-side wing presents at least one shaped segment that is shaped in such a manner that the length of the suction-side wing within this segment is shorter than the length of the suction-side wing at each end of this segment.

Leading edge shield

The invention provides a blade () comprising a blade body () made of organic matrix composite material reinforced by fibers and a leading edge shield () made of a material that withstands point impacts better than the composite material of the blade body. The leading edge shield () is assembled on the blade body () and the blade () includes bonding reinforcement () adhesively bonded on the leading edge shield () and on the blade body (). The invention also provides a turbojet including a fan including such blades, and also a method of fabricating such a blade.

Blade comprising a leading edge shield and method for producing the blade

Seal () 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 () in contact with a first blade adjacent to a first circumferential end of the platform, and a second part () in contact with a second blade adjacent to a second circumferential end of the platform, the first part () and the second part () of the seal () being fixed to each other such that a displacement in the circumferential direction of one of the two parts () of the seal () causes a displacement of the other part () of the seal () in the same direction, when the two parts () of the seal () are fixed to each other.

Inter-blade platform seal

A fiber preform for a turbine engine blade, the preform comprising a main fiber structure () obtained by a single piece of three-dimensional weaving, said main first structure () comprising a first longitudinal segment () suitable for forming a blade root, a second longitudinal segment () extending 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 () and suitable for forming a first tongue for a first platform, wherein the first transverse segment () extends axially over a length that is less than 30%, preferably less than 15%, of the length of the junction () between the first and second longitudinal segments ().

Preform and one-piece vane for turbomachine

The invention relates to comprising a blade body () made of composite material having a polymer matrix reinforced by fibers and a leading edge shield () made of material having greater ability to withstand point impacts than the composite material of the blade body. The leading edge shield () is assembled on the blade body () by means of a first adhesive () and a second adhesive (), both adhesives () being deposited between the blade body () and the leading edge shield (). Both adhesives () form respective continuous films between the blade body () and the leading edge shield ().

Blade comprising a blade body made of composite material and a leading-edge shield

The invention relates to the field of turbomachine blades, and more specifically to a leading-edge shield () for a turbomachine blade (), said leading-edge shield () having a pressure-side wing () and a suction-side wing (), each extending along a height and along a length, the wings being connected together over their height, the pressure-side wing () presenting a greater length than the suction-side wing () over a first segment (S) of the leading-edge shield (), and an equal or smaller length than the suction-side wing () over a second segment (S) of the leading-edge shield ().

A leading edge shield for a turbomachine blade extends heightwise from a bottom end to a top end, presents an outside face overlying a leading edge and an inside face for fastening to a blade body, and includes a pressure side wing, a suction side wing, and a central section joining together the pressure side wing and the suction side wing. Between the outside face and the inside face, the central section presents thickness that is greater than the thicknesses of the pressure side and suction side wings. The thickness of the central section increases with a gradient that is stable or increasing over a first segment from the bottom end of the leading-edge shield, but it presents a gradient that decreases beyond said first segment.

A leading-edge shield () for a turbomachine blade () includes a pressure-side wing () and a suction-side wing (). Each of the wings () extends along a height (H) from a bottom edge () to a top edge () and along a length, from the leading edge to a respective rear edge, and are connected together over the leading edge. At least one of the wings from among the suction-side wing () and the pressure-side wing () presents a segment (S), adjacent to the top edge () and extending over at least 10% of the height (H), wherein the rear edge () slopes towards the top edge ().

Blade, associated fan and turbojet engine

A blade made of organic matrix composite material for a gas turbine aeroengine, includes an airfoil extending transversely between a leading edge and a trailing edge; and a metal strip positioned on the leading edge of the airfoil, the metal strip having two flanges extending on either side of the leading edge over portions of the side faces of the airfoil forming a pressure side face and a suction side face so that the strip fits closely to the profile of the leading edge, the metal strip being fastened to the leading edge of the airfoil by at least one stitching thread; wherein the stitching thread has at least one external thread segment extending substantially transversely between a hole formed through a flange of the strip and a passage formed in a portion of the airfoil that has at least one face that is not covered by the metal strip.

Growing community of inventors

Moissy-Cramayel, France

Jérémy Guivarc'h