METHOD FOR CREATING AN AIRCRAFT TURBOMACHINE VANE USING ADDITIVE MANUFACTURING

Method for creating at least one aircraft turbomachine vane using additive manufacturing, the method comprising a step of additive manufacturing of said vane on beds of powder using selective laser melting, the manufacturing being performed on a support plate (180) so that first or second circumfere...

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Bibliographische Detailangaben
1. Verfasser:	VOIRON, MICKAEL
Format:	Patent
Sprache:	eng ; fre
Schlagworte:	ADDITIVE MANUFACTURING TECHNOLOGY ADDITIVE MANUFACTURING, i.e. MANUFACTURING OFTHREE-DIMENSIONAL [3-D] OBJECTS BY ADDITIVE DEPOSITION, ADDITIVEAGGLOMERATION OR ADDITIVE LAYERING, e.g. BY 3-D PRINTING,STEREOLITHOGRAPHY OR SELECTIVE LASER SINTERING BLASTING CASTING ENGINE PLANTS IN GENERAL HEATING LIGHTING MACHINES OR ENGINES IN GENERAL MAKING METALLIC POWDER MANUFACTURE OF ARTICLES FROM METALLIC POWDER MECHANICAL ENGINEERING NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES PERFORMING OPERATIONS POWDER METALLURGY STEAM ENGINES TRANSPORTING WEAPONS WORKING METALLIC POWDER
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Beschreibung
Zusammenfassung:	Method for creating at least one aircraft turbomachine vane using additive manufacturing, the method comprising a step of additive manufacturing of said vane on beds of powder using selective laser melting, the manufacturing being performed on a support plate (180) so that first or second circumferential edges are manufactured first directly on said support plate, at least one temporary-support member (26) being produced simultaneously with said first or second edges, at the level of said or of each blade, and extending between a support plate and the leading or trailing edges of the blade, and a step of removing the said support member by severing its connection with the associated leading or trailing edge, characterized in that removal is performed by means of a tool (30) at least one end of which is engaged in at least one recess (28) of said support member, and which is moved in pivoting in a plane substantially perpendicular to the associated leading or trailing edge. Procédé de réalisation par fabrication additive d'au moins une aube de turbomachine d'aéronef, le procédé comprenant une étape de fabrication additive par fusion laser sur lits de poudre de ladite aube, la fabrication étant réalisée sur un plateau support (180) de sorte que des premiers ou seconds bords circonférentiels soient fabriqués en premier directement sur ledit plateau support, au moins un organe (26) de soutien provisoire étant réalisé simultanément auxdits premiers ou seconds bords, au niveau de ladite ou de chaque pale, et s'étendant entre un plateau de support et les bord d'attaque ou de fuite de la pale, et une étape de retrait dudit organe de soutien organe de soutien en rompant sa liaison avec le bord d'attaque ou de fuite associé, caractérisé en ce que le retrait est réalisé au moyen d'un outil (30) dont au moins une extrémité est engagée dans au moins un évidement (28) dudit organe de soutien, et qui est déplacé par pivotement dans un plan sensiblement perpendiculaire au bord d'attaque ou de fuite associé.