Manufacture of blade passages of turbomachinery rotors

摘要

The present invention relates to a method for producing blade passages of turbomachinery rotors, in particular gas turbine rotors, with integrated vanes, comprising the steps of: producing a plurality of circumferentially staggered arrangements (10, 20, 30, 40) of bores (11-41) from a radially outer surface of the rotor forth, wherein at least two holes (11-15; 21-25; 31-35) of at least one arrangement in the axial and / or circumferential direction are offset from each other in such a way that these holes intermesh and form a slot; and - generating pressure and suction sides (2, 3) of blades by material removal in the slots.