FIELD: process engineering.
SUBSTANCE: invention relates to machine building, particularly to methods of producing aircraft gas turbine engine vanes from materials that can be deformed in cold or hot state. Vane preform is made. Aerodynamic profile is formed in every section of vane airfoil portion. Tail end is produced. Finishing jobs are performed. Producing aerodynamic profile and tail end is performed in simultaneous twisting of vane airfoil portion and tail end and sixing in die. Flat preform is produced with cross sections the area and length of which equal area of appropriate sections of stamped vane and length of chords of said sections.
EFFECT: reduced metal input and process time.
2 dwg, 1 ex
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