Safran Aircraft Engines

Safran

Safran Safran Aircraft Engines

Clément Pierre Postec

Thomas Alain De Gaillard

Vivien Mickaël Courtier

Vincent Joudon

Mattéo Minervino

François Charleux

Guillaume Pascal Jean-Charles Gondre

Eddy Keomorakott Souryavongsa

Teddy Fixy

Pierre Jean Faivre D'arcier

Vivien Mickael Courtier

Charles-Henri Claude Jacky Sullet

Pierre-Antoine Gérard Joseph Barbier

Vincent Lionel René Maison

Pierre Jean Faivre D′Arcier

A propeller blade or airfoil of a turboprop of composite material includes a fibrous reinforcement densified by a matrix, the propeller blade or airfoil including, in a span direction, a root and an aerodynamic profile. The fibrous reinforcement includes a fibrous preform having a three-dimensional weave with a root preform portion present in the root and an aerodynamic preform portion present in the aerodynamic profile, the root and aerodynamic preform portions being linked to one another by the three-dimensional weave. The root preform portion of the fibrous preform includes an unlinked area delimiting an internal root recess forming a cavity opening at a free end of the root.

Propeller blade or airfoil with hollow composite root

A propeller blade or airfoil for a turboprop engine made from composite material including a matrix-densified fibrous reinforcement, the propeller blade or airfoil including, in the direction of its span, a root and an aerodynamic profile. The fibrous reinforcement includes a fibrous preform having three-dimensional weaving with a root preform portion and an aerodynamic profile preform portion. The fibrous preform includes a separation delimiting a recess that forms a cavity extending both into the root and into the aerodynamic profile. A spar is present in the cavity, the spar including an aerodynamic profile shaping portion positioned in a first portion of the cavity and a root shaping portion positioned in a second portion of the cavity. The root has a rotationally symmetric shape.

Propeller blade or vane having a hollow composite root

A turboprop engine blade or propeller airfoil made of composite material includes a fiber reinforcement densified by a matrix, the blade or propeller airfoil including along a longitudinal direction a root and an aerodynamic profile. The fiber reinforcement includes a fiber preform having a three-dimensional weave with a root preform part located in the root and an aerodynamic profile part located in the aerodynamic profile, the root preform and aerodynamic profile parts being connected to one another by three-dimensional weaving. The root preform part includes two woven skins wound around an insertion element.

Propeller blade or airfoil with wound composite root

The present invention relates to a blade () comprising: —a composite material structure (), —a blade root fastening portion () further comprising a shoulder () extending into the recess from the wall —a base () arranged in the recess and comprising a support member configured to abut against the shoulder () of the blade root fastening portion () and a passage () formed in the support member, the sections () of the blade root portion () of the composite material structure extending through the passage (), and —a blocking part () arranged in the recess between the two sections () of the blade root portion () such that each section of the blade root portion () is pressed against the support member by the blocking part ().

Blade comprising a composite material structure and associated manufacturing method

An unducted fan having variable pitch blades for an aircraft or wind propulsion system is described. The fan includes a hub provided with housings pivotally receiving vanes about radial axes, and an outer casing of the hub into which circular openings of the housings open. Each vane includes a root which is rotatably mounted in the associated housing, a radially oriented blade and a disc-shaped platform extending from the blade to an edge of the circular opening. The blade includes at least one skin which includes a free lower edge facing the side of the root, wherein the platform is attached to the free lower edge of the skin.

Unducted fan having variable pitch blades comprising reduced disturbance platforms

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

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

The present invention relates to a blower vane of a turbomachine, comprising a structure made of composite material which comprises a fibrous reinforcement and a matrix in which the fibrous reinforcement is embedded. The vane comprises a first rigidification insert which extends in a first direction and at least one second insert which is connected to the first in a second direction which is non-collinear with the first direction, the first insert projecting from the vane in order to be connected to a disc of a turbomachine element.

Blower vane

A fibrous texture intended to form the fibrous reinforcement of a turbomachine blade made of composite material including a fibrous reinforcement densified by a matrix, wherein the fibrous texture includes an area of reduced stiffness including warp yarns or strands made of second fibers having a second elongation at break greater than the first elongation at break, the area of reduced stiffness extending in the longitudinal direction from the stilt area and up to a height less than or equal to 30% of the height of the blade, extending in the transverse direction between a first area and a second area, the first area extending over a first length from a first edge of the texture intended to form a leading edge, and the second area extending over a second length from a second edge of the texture intended to form a trailing edge.

Fibrous texture for manufacturing a fan blade made of composite material

A blade body made of composite material includes fiber reinforcement densified by a matrix, the blade body extending in a longitudinal direction between a root or bottom portion and a tip or top portion, and in a transverse direction between a leading edge and a trailing edge. The fiber reinforcement of the blade body includes a first portion constituted by a plurality of yarn layers interlinked by three-dimensional or multilayer weaving, and a second portion forming all or part of at least one leading edge or at least one trailing edge of a blade. The second portion includes a plurality of short fibers oriented in random manner, the yarns of the plurality of yarn layers of the first portion and the short fibers of the second portion being embedded in the matrix.

Blade body and a blade made of composite material having fiber reinforcement made up both of three-dimensional weaving and also of short fibers, and method of fabrication

Growing community of inventors

Moissy-Cramayel, France

Clément Pierre Postec