Snecma

Safran Aircraft Engines

Safran

Messier-Bugatti-Dowty

Albany Engineered Composites, Inc.

Bruno Jacques Gerard Dambrine

Thierry Godon

Dominique Coupe

Jean-Noel Mahieu

Jonathan Goering

Ludovic Edmond Camille Molliex

Dominique Marie Christian Coupe

Michael Podgorski

Stephane Rousselin

Yann Marchal

Dominique Magnaudeix

Didier Rene Andre Escure

Francois Marie Paul Marlin

Son Le Hong

Antoine Phelippeau

Yann Didier Simon Marchal

Philippe Verseux

Alain Robert Yves Perroux

Brock Gilbertson

Franck Bernard Leon Varin

Alain Paul Madec

Olivier Michael Molinari

Caroline Aumont

Sylvain Didier Leclercq

Jean-Francois Fromentin

Beryl Cassandre Anne Mereaux

Fabienne Lacorre

Jean-Yves Guedou

Ken Ouellette

Stephane Andre Leveque

Sandrine Chatel

There is provided a method of fabricating a blade platform out of composite material with integrated gaskets for a turbine engine fan, the platform including a base and a stiffener, the method including using three-dimensional weaving to make a single-piece fiber blank with a plurality of longitudinal yarn layers extending in a direction corresponding to a longitudinal direction of the base of the platform; shaping the fiber blank to form a fiber preform having a first portion forming a base preform and a second portion forming a stiffener preform; positioning platform gaskets at side margins of the first portion of the fiber preform forming a base preform; placing the fiber preform with the gaskets in an injection mold; injecting resin into the injection mold; compacting the assembly; heating the injection mold to solidify the resin; and unmolding the resulting platform.

Method of fabricating a blade platform out of composite material with integrated gaskets for a turbine engine fan

A method of fastening structural metal reinforcement on a portion of a gas turbine blade made of composite material and an injection mold for performing the method, the method including positioning the structural metal reinforcement in an injection mold, positioning the portion of the blade onto which the structural metal reinforcement is to be fastened in the injection mold, the portion of the blade and the structural metal reinforcement being positioned relative to each other in their final relative position while leaving between them a gap, injecting adhesive into the gap between the structural metal reinforcement and the portion of the blade onto which the structural metal reinforcement is to be fastened, and polymerizing the adhesive.

Method of fastening structural metal reinforcement on a portion of a gas turbine blade made of composite material, and an injection mold for performing such a method

A fiber preform for a hollow turbine engine vane, the preform including a main fiber structure obtained by three-dimensional weaving and including at least one main part, wherein the main part extends from a first link strip, includes a first main longitudinal portion forming a pressure side wall of an airfoil, an U-turn bend portion forming a leading edge or a trailing edge of the airfoil, a second main longitudinal portion facing the first main longitudinal portion and forming a suction side wall of the airfoil, and terminating at a second link strip. The first and second link strips are secured to each other and form a link portion of the main fiber structure. The main longitudinal portions are spaced apart so as to form a gap between the main longitudinal portions forming a hollow in the airfoil.

Fiber preform for a hollow turbine engine vane

A turbine engine blade made of composite material including fiber reinforcement obtained by weaving a first plurality of yarns with a second plurality of yarns, the yarns of the first plurality of yarns being arranged in successive layers and extending in a longitudinal direction of the fiber blank corresponding to a longitudinal direction of the blade, the reinforcement being densified by a matrix. The blade includes one or more internal channels extending in the longitudinal direction of the blade.

Method of fabricating a composite material blade having internal channels, and a composite material turbine engine blade

An oxide/oxide composite material turbomachine blade including a fiber reinforcement obtained by weaving a first plurality of threads and a second plurality of threads, with the threads of said first plurality of threads being arranged in successive layers and extending in the longitudinal direction of the fiber blank corresponding to the longitudinal direction of the blade is disclosed. The reinforcement is densified by a matrix, with the blade further including one or several internal channels having a coiled shape extending in the longitudinal direction of the blade.

Method for manufacturing an oxide/oxide composite material turbomachine blade provided with internal channels

A method of making a fiber preform, and the preform, for fabricating a turbine engine blade out of composite material, the method including: making a single-piece fiber blank by three-dimensional weaving with layers of longitudinal yarns interlinked by yarns of layers of transverse yarns; and shaping the fiber blank to obtain a single-piece fiber preform including a portion forming an airfoil preform and at least one portion forming a platform preform. During weaving, yarns of a first group of longitudinal yarns are extracted from the fiber blank beside one of side faces of the blank to form a portion corresponding to a blade platform preform, and yarns of a second group of longitudinal yarns are inserted into the fiber blank with mutual crossing of the yarns of the first group and the yarns of the second group.

Fiber preform for a turbine engine blade made of composite material and having an integrated platform, and a method of making it

A fiber structure reinforcing a composite material part woven as a single piece by multilayer weaving between plural first and second layers of yarns. The fiber structure includes a portion of decreasing thickness that presents: plural yarn withdrawal parts in surface continuity, with yarns interrupted from the first plural layers of yarns underlying the layer of yarns of the first plural layers of yarns situated in the surface of the structure; and plural yarn withdrawal parts in surface discontinuity, with yarns interrupted from the first plural layers of yarns situated at the surface of the structure, each interrupted yarn replaced in the surface of the structure by a yarn of a layer of yarns underlying the first plural layers of yarns. The yarns of the second plural layers of yarns situated in the surface of the fiber structure are continuous over at least the entire portion of decreasing thickness.

Fibrous reinforcement structure for composite material part having a reduced thickness portion

A fiber structure for reinforcing a composite material part, the structure being woven as a single piece by multilayer weaving between a first plurality of layers of yarns extending in a first direction and a second plurality of layers of yarns extending in a second direction. The second plurality of layers of yarns includes at least one layer of variable-weight yarns, each variable-weight yarn including a separable assembly of individual yarns, each having a determined weight. The fiber structure includes at least one portion of reduced thickness in which the variable-weight yarn presents a weight that is less than the weight that it presents prior to the reduced thickness portion.

Fibrous structure having variable numbering yarns

A fiber structure made as a single piece by multilayer weaving using a method including weaving warp yarns of at least a first set of layers of warp yarns with weft yarns including at least some that are woven with extra length so as to have warp yarn end portions available that extend beyond the zone of weaving, the warp yarn end portions being returned to be woven with warp yarns by being reinserted in layers of warp yarns, and a hollow, or tubular, portion being formed by looping the first woven set of layers of warp yarns back onto itself and applying traction to the ends of the reinserted weft yarns so that a fiber preform for a part including a hollow portion can be obtained as a single piece.

Multilayer woven fibrous structure including a hollow tubular part, production method thereof and composite part comprising same

The invention relates to fiber reinforcement for making an elongate mechanical part () out of composite material having a lug () at at least one end for receiving a pin for making a pivot connection with another part, the fiber reinforcement being made from a central fiber structure (') for forming a core that is obtained by three-dimensional weaving, from a peripheral fiber structure (&#x2032;) that is to form a belt surrounding the central structure so as to form at least one empty cylindrical space in the lug of the part, and from at least one annular fiber structure (&#x2033;) that is to form a ring that is formed inside the empty space provided between the central structure and the peripheral structure.

Fiber reinforcement for making an elongate mechanical part out of composite material

A reinforcing fiber structure woven as a single piece for fabricating a composite material part and including: first and second fiber substructures, each fiber substructure including at least one independent portion obtained by multilayer weaving between a plurality of layers of warp yarns and a plurality of layers of weft yarns that are independent from the other substructure; and an assembly portion between the least first and second fiber substructures in which a plurality of adjacent layers of warp yarns of the first fiber substructure are interlinked by at least some of the warp yarns of the second fiber substructure.

Fibrous structure for a part made of a composite material and having a complex shape

A reinforcing fiber structure for a composite material part is woven as a single piece by multilayer weaving between plural layers of weft yarns and plural layers of warp yarns arranged in adjacent manner between two faces of the structure. The fiber structure includes at least one arcuate portion extending over one of the faces of the fiber structure, the arcuate portion including at least some of the warp yarns continuous with at least two adjacent warp yarn layers present on one of the faces of the structure. The warp yarns of the arcuate portion are of a length that is longer than the warp yarns of at least two underlying warp yarn layers of the structure. In addition, the warp yarns of the arcuate portion are not interlinked with other warp yarns of the fiber structure.

Fibrous structure for a part made of composite material having one or more archshaped portions

A process for manufacturing a one-piece axisymmetric part includes: superposition, around a rotating cylindrical mandrel of at least respectively inner and outer metal-coated composite fibrous structures, wound in first and second crossed directions on the mandrel; arranging, between the crossed inner and outer fibrous structures, at least one layer of metallic wire; then placing a blank of the part, formed by the fibrous structures and the layer of metallic wire, in a tool to apply to the blank a hot isostatic pressing treatment, and to obtain the part.

Process for manufacturing a one-piece axisymmetric metallic part from composite fibrous structures

A method for manufacturing a metal part by producing a preform with a fibrous structure of metal fibers, and subjecting the preform to hot isostatic pressing in a tool until a solid part is obtained, the tool including at least one first element including a cavity for molding the part. The first tool element is elongate in a direction between two ends, and the fibrous structure is at least partially formed by winding at least one metal wire around the first tool element in the direction, from one end to the other. The method can be used, for example, for manufacturing reinforcement parts for a fan blade of a turbojet engine.

Method for manufacturing a metal part

A jacquard type loom for making a fabric by weaving plural warp yarns with plural weft yarns, the fabric including a determined number of columns of warp yarns per unit length and a determined number of layers of weft yarns. The loom includes a comber board including plural holes passing a corresponding number of control cords, each control cord including an heddle eye through which a warp yarn passes. The holes are distributed in a determined number of columns extending parallel to the warp yarn direction and a determined number of rows per column extending in a direction perpendicular to the warp yarn direction. The comber board includes a number of columns of holes per unit length smaller than the number of warp columns in the same unit length in the fabric, and a number of rows of holes greater than the number of warp layers in the fabric.

Growing community of inventors

Le Chatelet en Brie, France

Bruno Jacques Gerard Dambrine