Safran

Snecma

Sebastien Pautard

Wouter Balk

Jean-Pierre Lombard

Nicolas Pierre Lanfant

Maxime Briend

Benjamin Samson

Benjamin Kiener-Calvet

Frederic Rogues

A method of fabricating a blade of composite material having an incorporated metal leading edge for a gas turbine aeroengine, the method including in succession placing a metal strip for making the leading edge of a blade in a cavity of an injection mold for making the blade, closing the injection mold, injecting a thermoplastic resin under pressure into the cavity of the mold so as to shape and overmold the metal strip, compacting the assembly, solidifying the resin by regulating the temperature of the injection mold, and unmolding the resulting blade.

Method of fabricating a composite material blade having an integrated metal leading edge for a gas turbine aeroengine

The invention relates to a turbine engine vane comprising a main body made of composite material, a leading edge, a trailing edge, and at least one metal structural reinforcement, the structural reinforcement comprising a junction surface portion connected to the main body, the structural reinforcement extending between the junction surface portion and one of the leading or trailing edges, the vane being characterized in that the profile of the junction surface portion of the structural reinforcement has a camber less than 30%.

Turbine engine vane with asymmetrical profile

A link part for a turbine engine which mounted between a fan cone and a fan disk supporting fan blades is provided. The link part includes an annular wall pierced by a plurality of orifices, each orifice for receiving a fastener member and terminated by a substantially perpendicular rim having an outer surface that provides an aerodynamic extension of the fan between an outer surface of the fan cone and an outer surface of a fan blade platform. The annular wall is made of a first material that is composite and is provided on an inner surface of the rim with a ring made of a second material that is different from the first and that is suitable for radially retaining the fan blade platform.

Axisymmetric part for an aviation turbine engine rotor

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Palaiseau, France

Sebastien Pautard