Snecma

Snecma Moteurs

Herakles

Stephane Blanchard

Dominique Coupe

Clement Roussille

Romain Nunez

Guillaume Renon

Thierry Pancou

Eric Conete

Alain Dominique Gendraud

Antoine Jean-Philippe Beaujard

Guillaume Sevi

Georges Habarou

Pierre Camy

Elric Georges André Fremont

Claude Corbin

Stéphane Touchaud

Herve Barret

A turbine engine blade made of composite material including fiber reinforcement densified by a matrix is fabricated by a method including: performing three-dimensional weaving to make a single-piece fiber blank; shaping the fiber blank to obtain a single-piece fiber preform having a first portion forming a preform for a blade root and an airfoil, at least one second portion forming a preform for a blade inner platform or for wipers of a blade outer platform, and at least one third portion forming a preform for reinforcing a blade inner platform or for overhangs of a blade outer platform; and densifying the fiber preform with a matrix to obtain a composite material blade having fiber reinforcement constituted by the preform and densified by the matrix, and forming a single piece with an inner and/or outer platform incorporated therein.

Turbine engine blade made of composite material, and a method of fabricating it

A method for fabricating turbine engine blade or vane made of composite material includes: performing three-dimensional weaving to make a single-piece fiber blank; shaping the fiber blank to obtain a single-piece fiber preform having a first portion forming a preform for at least a blade/vane airfoil, at least one second portion forming a preform for an inner part of a blade/vane inner platform or for an outer part of a blade/vane outer platform, and at least one third portion forming a preform for an outer part of a blade/vane inner platform or for an inner part of a blade/vane outer platform; and densifying the fiber preform with a matrix to obtain a composite material blade, and forming a single piece with an inner and/or outer platform(s) incorporated therein.

Turbine engine blade or vane made of composite material, turbine nozzle or compressor stator incorporating such vanes and method of fabricating same

A turbomachine rotor wheel including blades made of composite material; an annular mounting plate; a plurality of composite material blades mounted on the mounting plate, each blade also including a top platform at its tip carrying radial labyrinth teeth; an orientation disk fastened coaxially around the mounting plate and including at its outer periphery a plurality of axial slots that are open at one end, each slot presenting a cross-section that matches the cross-section of a blade root so as to hold it angularly in position by co-operation of shapes; and a variable-diameter spring ring housed in part in an axial notch formed in each blade root and projecting axially relative thereto, the spring ring to come into radial abutment against an inside surface of the orientation disk during radial outward movement of the blades relative to the mounting plate.

Turbine engine rotor wheel with blades made of a composite material provided with a spring ring

A support arm () is intended to be installed in a radial position in an afterburner device of a bypass turbojet. The device comprises first and second inner annular casings defining a passage for a primary flow and an outer annular casing defining together with the first inner annular casing a passage for a secondary flow. The arm () comprises a monobloc structure made of composite material including two integral walls (), on the one hand, designed to define a groove () having a substantially V-shaped profile and, on the other hand, including first end parts () joined together and adapted to define a foot () and second end parts () adapted each to define at least one flange () intended to be positively connected to the outer annular casing.

Monobloc flameholder arm for an afterburner device of a bypass turbojet

A controlled hot flap shutter for a turbojet nozzle includes a friction surface made of metal, and including straight lateral flanks to reduce the gap between each controlled hot flap shutter and the tracking flap shutters adjacent thereto.

Turbojet axisymmetric nozzle controlled hot flap shutter

Growing community of inventors

Chartrettes, France

Stephane Blanchard