Safran Aircraft Engines

Vivien Mickael Courtier

Anthony Binder

Laurent Jablonski

Regis Eugene Henri Servant

Vincent Joudon

Clément Pierre Postec

Eddy Keomorakott Souryavongsa

Teddy Fixy

Clement Cottet

The invention relates to a composite blade () for a turbine engine rotor, for example, an unducted propeller, comprising a skin () made of woven fibres forming the outer profile of the blade and an attachment () with cylindrical geometry in the direction of the span emerging from the blade root (), which attachment is intended to retain the blade () on a hub of the rotor, characterised in that it further comprises a spar () having a hollow tube structure made of braided carbon fibres, fixed to the attachment () and extending inside the skin () over at least part of the span of the blade (). The invention also relates to a propeller comprising said blade and to a method for manufacturing said blade.

Composite blade for a turbine engine rotor

An assembly comprising a propeller blade and its system for angularly adjusting the pitch of the blade including a bowl which is radially delimited by an annular wall extending about an axis for adjusting the pitch of the blade, the bowl having a bottom wall, a free lower end of the root being fitted axially into a complementary housing of the bottom wall in order to rotatably connect the bowl and the blade about the pitch-adjustment axis. The root of the blade comprises a first limiting face that engages with a first abutment face of the bowl to limit the rotation of the blade in the event of breakage of the lower end of the root.

Aircraft turbine engine comprising variable-pitch propeller blades

Fan or propeller vane () for an aircraft turbomachine, the vane being made from a composite material and comprising a blade () and a base (), the base being formed by a longitudinal end () of a spar () which is formed by a fibrous reinforcement formed from threads woven in three dimensions and a portion () of which extends inside the blade (), the blade () having an aerodynamic profile which is defined by a skin () which is formed by woven threads and which surrounds the portion of the spar, the spar () and the skin () being embedded in a polymerised resin, characterised in that the portion () of the spar comprises projecting longitudinal stiffening members () which together delimit spaces () for receiving longitudinal inserts () which are formed from a honeycomb material.

Fan or propeller vane for an aircraft turbomachine and method for manufacturing same

A blade is provided including a structure made of composite material including a fibrous reinforcement obtained by three-dimensional weaving and a matrix in which the fibrous reinforcement is embedded, the structure made of composite material including an aerodynamically profiled blade portion and a blade root portion, the blade root portion including two sections each connected to the blade portion, a blade root fastening part including a wall delimiting a cavity and an opening formed in the wall, the structure made of composite material extending through the opening so that the blade portion is located outside the fastening part and the blade root portion is located inside the cavity, and a blocking part disposed in the cavity, between the two sections of the blade root portion, in order to keep the two sections apart from each other so as to oppose withdrawal of the blade root portion from the cavity via the opening.

Growing community of inventors

Moissy-Cramayel, France

Vivien Mickael Courtier