METHOD FOR MANUFACTURING A TURBOMACHINE COMPRESSOR BLADE BY COMPACTING

The invention relates to a method for producing a turbomachine compressor blade, comprising the following steps: - installing primary pins (26) comprising a material other than a titanium-based alloy in primary bores (20) of a core, the primary bores forming at least one polygon, and installing a se...

Ausführliche Beschreibung

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Bibliographische Detailangaben
Hauptverfasser:	PEREIRA, Axel, GIMEL, Alexandre, RICHARD, Jean-François, GLEIZE, Christophe, SALMON, Jérôme
Format:	Patent
Sprache:	eng ; fre
Schlagworte:	BLASTING CLADDING OR PLATING BY SOLDERING OR WELDING COMBINED OPERATIONS CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING ENGINE PLANTS IN GENERAL HEATING LIGHTING MACHINE TOOLS MACHINES OR ENGINES IN GENERAL MECHANICAL ENGINEERING MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVINGMATERIAL METAL-WORKING NOT OTHERWISE PROVIDED FOR NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES NON-POSITIVE DISPLACEMENT PUMPS OTHER WORKING OF METAL PERFORMING OPERATIONS POSITIVE DISPLACEMENT MACHINES FOR LIQUIDS PUMPS FOR LIQUIDS OR ELASTIC FLUIDS PUNCHING METAL SOLDERING OR UNSOLDERING STEAM ENGINES TRANSPORTING UNIVERSAL MACHINE TOOLS WEAPONS WELDING WORKING BY LASER BEAM WORKING OR PROCESSING OF SHEET METAL OR METAL TUBES, RODS ORPROFILES WITHOUT ESSENTIALLY REMOVING MATERIAL
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Beschreibung
Zusammenfassung:	The invention relates to a method for producing a turbomachine compressor blade, comprising the following steps: - installing primary pins (26) comprising a material other than a titanium-based alloy in primary bores (20) of a core, the primary bores forming at least one polygon, and installing a secondary pin made of titanium-based alloy in a secondary bore of the core; - producing a stack (2) of a suction-face sheet (4), a core (14) and a pressure-face sheet (6); - compacting the stack; - removing the primary pins (26) from the primary bores (20); - removing the secondary pin from the secondary bore; and - taking the core (14) away from the stack. Le procédé de fabrication d'une aube de compresseur de turbomachine comprend les étapes suivantes : - installer des pions primaires (26) comprenant un matériau autre qu'un alliage à base de titane dans des alésages primaires (20) d'un noyau, les alésages primaires formant au moins un polygone, et installer un pion secondaire en alliage à base de titane dans un alésage secondaire du noyau, - réaliser un empilement (2) d'une tôle d'extrados (4), du noyau (14) et d'une tôle d'intrados (6), - compacter l'empilement, - éliminer les pions primaires (26) des alésages primaires (20), - éliminer le pion secondaire de l'alésage secondaire, et - ôter le noyau (14) de l'empilement.