METHOD FOR PRODUCING A METAL BLADED ELEMENT FOR A TURBOMACHINE OF AN AIRCRAFT

The invention relates to a method for producing a metal bladed element for a turbomachine of an aircraft, said bladed element comprising at least one blade having a lower surface and an upper surface extending between a leading edge and a trailing edge of the blade, the trailing edge having to have...

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Bibliographische Detailangaben
Hauptverfasser:	SOISSON, Marc, GIMEL, Alexandre, BOUKERMA, Saïd, LISOWSKI, Janusz, SABOUNDJI, Amar
Format:	Patent
Sprache:	eng ; fre
Schlagworte:	BLASTING CHEMICAL SURFACE TREATMENT CHEMISTRY COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATIONOR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL COATING MATERIAL WITH METALLIC MATERIAL COATING METALLIC MATERIAL COMBINED OPERATIONS DIFFUSION TREATMENT OF METALLIC MATERIAL ENGINE PLANTS IN GENERAL HEATING INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION INGENERAL LIGHTING MACHINE TOOLS MACHINES OR ENGINES IN GENERAL MEASURING MECHANICAL ENGINEERING METAL-WORKING NOT OTHERWISE PROVIDED FOR METALLURGY MULTI-STEP PROCESSES FOR SURFACE TREATMENT OF METALLICMATERIAL INVOLVING AT LEAST ONE PROCESS PROVIDED FOR IN CLASSC23 AND AT LEAST ONEPROCESS COVERED BY SUBCLASS C21D OR C22F OR CLASS C25 NON-MECHANICAL REMOVAL OF METALLIC MATERIAL FROM SURFACE NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES OTHER WORKING OF METAL PERFORMING OPERATIONS PHYSICS STEAM ENGINES TESTING TESTING STATIC OR DYNAMIC BALANCE OF MACHINES ORSTRUCTURES TESTING STRUCTURES OR APPARATUS NOT OTHERWISE PROVIDED FOR TRANSPORTING UNIVERSAL MACHINE TOOLS WEAPONS
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Beschreibung
Zusammenfassung:	The invention relates to a method for producing a metal bladed element for a turbomachine of an aircraft, said bladed element comprising at least one blade having a lower surface and an upper surface extending between a leading edge and a trailing edge of the blade, the trailing edge having to have a thickness X1, said method comprising the steps of: a) producing the bladed element by lost-wax casting, and b) finishing the bladed element, characterised in that step b) comprises the chemical milling at least of the trailing edge of the or each blade so as to obtain said thickness X1 which cannot be directly obtained by step a). Procédé de fabrication d'un élément aubagé métallique pour une turbomachine d'aéronef, cet élément aubagé comportant au moins une pale comportant un intrados et un extrados s'étendant entre un bord d'attaque et un bord de fuite de la pale, le bord de fuite devant avoir une épaisseur X1, le procédé comportant les étapes de : a) fabrication de l'élément aubagé par fonderie à la cire perdue, et b) finition de l'élément aubagé, caractérisé en ce que l'étape b) comprend l'usinage chimique au moins du bord de fuite de la ou de chaque pale de façon à obtenir ladite épaisseur X1 qui ne peut être obtenue directement par l'étape a).