Safran Aircraft Engines

Richard Anandavelou Mounien

Lucas Antoine Christophe Lauwick

Pierre-Alexis Poulet

Antoine Galve

Manon Commarmot

Henri Outtrabady

A method for manufacturing an inter-blade platform of a turbomachine fan, the platform including a base including a first and a second sacrificial lateral edge having a thickness smaller than that of the central part of the base, the method including the production of a preform of the platform by three-dimensional weaving including a central part portion and two sacrificial edge portions, the thickness of which is smaller than that of the central part portion, the difference in thickness between the lateral edge portions and the central part portion being achieved by withdrawing a plurality of weft yarns located outside the central part portion and not being woven with warp yarns.

Method for manufacturing an inter-blade platform with sacrificial edges

A method for manufacturing a blade of a fan for an aircraft turbomachine extending around a longitudinal axis, the blade including an aerofoil made of a composite material having a leading edge and a trailing edge connected by a pressure side and a suction side, the aerofoil extending between a base and a free end, the method including each of the following steps: —pairing and bonding a metal shield to the leading edge, —obtaining a first measurement of a radial moment weight of the blade before or after the metal shield has been bonded to the leading edge and determining a machining kerf, —machining the free end and/or the trailing edge along the machining kerf so as to adjust the mass and radial moment weight of the blade, —obtaining a second measurement of the radial moment weight of the blade.

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MOISSY-CRAMAYEL, France

Richard Anandavelou Mounien