METHOD FOR PRODUCING COMPOSITE BLADE CLEATS FOR AN AIRCRAFT TURBINE ENGINE

The invention relates to a method (10) for manufacturing composite blade cleats for an aircraft turbine engine, comprising: - the provision (12, 14) of a woven panel (24), comprising a plurality of cleat preforms (30) each having a working part (32) and at least one margin (34), the preforms (30) be...

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Bibliographische Detailangaben
Hauptverfasser:	MARCHAL, Yann, LE CLOAREC, Damien, COUPE, Dominique
Format:	Patent
Sprache:	eng ; fre
Schlagworte:	AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING INDEXING SCHEME ASSOCIATED WITH SUBCLASS B29C, RELATING TO PARTICULARARTICLES MAKING GRANULES OR PREFORMS PERFORMING OPERATIONS PREPARATION OR PRETREATMENT OF THE MATERIAL TO BESHAPED RECOVERY OF PLASTICS OR OTHER CONSTITUENTS OF WASTE MATERIALCONTAINING PLASTICS SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDEDFOR SHAPING OR JOINING OF PLASTICS TRANSPORTING WORKING OF PLASTICS WORKING OF SUBSTANCES IN A PLASTIC STATE, IN GENERAL
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Beschreibung
Zusammenfassung:	The invention relates to a method (10) for manufacturing composite blade cleats for an aircraft turbine engine, comprising: - the provision (12, 14) of a woven panel (24), comprising a plurality of cleat preforms (30) each having a working part (32) and at least one margin (34), the preforms (30) being distributed in the panel (24) in such a way that two adjacent preforms (30) share at least a part of the margin (34); the injection (16) of a matrix onto the panel (24); - after injection, the division (18) of the panel (24) in order to separate the cleats from one another; - the machining (20) of the cleats in order to remove the margins (34). Procédé de fabrication (10) de cales d'aubes composites pour une turbomachine d'aéronef, comprenant: - la fourniture (12, 14) d'un panneau (24), tissé, comprenant une pluralité de préformes de cales (30) ayant chacune une partie utile (32) et au moins une marge (34), les préformes (30) étant réparties dans le panneau (24) de sorte que deux préformes (30) adjacentes ont au moins une partie de ladite marge (34) en commun; - l'injection (16) d'une matrice sur le panneau (24); - après l'injection, la division (18) du panneau (24) afin de séparer les cales les unes des autres; - l'usinage (20) des cales pour retirer les marges (34).