METHOD FOR MANUFACTURING BLADE OF GAS TURBINE COMPRESSOR

摘要

PURPOSE: A method for manufacturing blade of gas turbine compressor is provided which is capable of preventing fracture or lapping of the work in the process of forging a work. CONSTITUTION: The method for manufacturing blade of gas turbine compressor comprises an extrusion step of forming first part(41) and second part(42) on a work(40); an up-set step of dividingly forming a boundary surface(43) between the first part corresponding to root platform of blade and the second part; a preform step of forming the first part, second part and boundary surface in a shape resembling shape of the final blade; and a final step of forming the work in a final processing shape, wherein the up-set step comprises the process of forming a shoulder(45) between the second part and the boundary surface in such a manner that the shoulder is extended in a continuous curve shape so that inflection point is not formed on a part where the second part and the boundary surface are contacted with each other.