Snecma

Safran Aircraft Engines

Safran Ceramics

Herakles

David Marsal

Adrien Jacques Philippe Fabre

Clément Roussille

Eric Bouillon

Jean-Marc Claude Perrollaz

Julien Mateo

Jean-Noel Mahieu

Lisa Pin

Gaël Frédéric Claude Cyrille Evain

Aurélia Clerambourg

Stéphane Otin

Ivan Herraiz

Etienne Juchauld

Pierre-Louis Alexandre Carlos

Nicolas Horn

Gilles Ansorena

Jérémy Blachier

Alain Foucault

Mathieu Louis Leduc

Gael Frederic Evain

Claire Charlotte Groleau

A part made of composite material includes fiber reinforcement including silicon carbide fibers presenting an oxygen content less than or equal to 1 % in atomic percentage; and a matrix present in the pores of the fiber reinforcement and including at least one sintered silicate phase including at least one rare earth silicate, mullite, or a mixture of mullite and of at least one rare earth silicate, the matrix including at least a first phase including mullite and a second phase, different from the first phase, including at least one rare earth silicate.

Composite material part

A method of fabricating a turbine engine blade out of composite material including fiber reinforcement densified by a matrix, the method including using multilayer weaving to make a first fiber that has a first portion forming a blade root preform and extended by a second portion, the second portion forming a tenon preform; using multilayer weaving to make a second fiber preform, the second preform including a first portion made up of two skins defining between them an internal housing, the first portion forming an airfoil preform, and a second portion extending from an outside surface of the skins, the second portion forming a platform preform; assembling the first preform with the second preform in the non-consolidated state by engaging the second portion of the first preform in the internal housing; and co-densifying the first and second preforms as assembled together in this way to obtain a turbine engine blade.

Method for manufacturing a turbomachine blade made of composite material

A blade including a structure with aerodynamic profile including two opposite skins obtained by three-dimensional weaving of a fibrous reinforcement densified by a matrix, and a longeron including a fibrous reinforcement obtained by three-dimensional weaving and densified by a matrix, the longeron including a first part extending outside the structure with aerodynamic profile and designed to be connected to a drive hub in rotation of the blade and a second part arranged inside the structure with aerodynamic profile between the two skins. The second part of the longeron has a thickness substantially similar to that of the skins of the structure with aerodynamic profile. In addition, the fibrous reinforcement of the second part of the longeron has the same weaving armor as that of the reinforcement of the skins of the structure with aerodynamic profile.

Blade having an integrated composite spar

A turbine engine blade of composite material comprising fiber reinforcement obtained by multilayer weaving of yarns and densified by a matrix. The blade has a first portion constituting an airfoil forming a single piece with at least one second portion constituting a blade root. The fiber reinforcement portions corresponding to the first and second portions of the blade are mutually interleaved, at least in part, with yarns of the second fiber reinforcement portion penetrating into the first fiber reinforcement portion.

Composite turbomachine blade with in-built root

An airfoil attachment including a support and flanks rising on it to delimit a broach compartment designed to receive and hold an airfoil root is provided. The flanks are machined so as to separate the portions and prevent a complete break of a flank and detachment of the airfoil when a crack develops because the crack is stopped by one of the notches.

Airfoil attachment holding an airfoil root in a broach fitting

A first insert () forming a ring is placed inside and in contact with a core () in degradable material. On the outer face of the core a plurality of inserts () is arranged each comprising a platform () applied against the outer face of the core and at least one blade () extending substantially radially outwards. A fibrous structure () is wound around the core passing over the platforms () and over the inner surface of the ring-shaped insert (). Molding of the fibrous structure, impregnated with a composition containing a resin, is performed before polymerization of the resin and removal of the core.

Method to manufacture a hollow, single-piece bladed disc

Growing community of inventors

Saint Aubin De Medoc, France

David Marsal