METHOD TO PROCESS COOLING HOLE OF GASTURBINE BLADE

摘要

A method for forming a cooling hole of a gas turbine blade is provided to improve machining accuracy by employing discharge processing method. A method for forming a cooling hole of a gas turbine blade comprises a step of testing the performance of the internal profile of a blade cooling hole and determines the internal profile of the cooling hole(S1), a step of processing an electrode to form a cooling hole in the determined shape(S2), a step of making an airfoil support jig and a shank support jig(S3), a step of forming a plurality of straight holes in the shank part of the blade by using an EDM(Electronic Discharge Machine) super drill(S4), a step of forming a shank cooling hole in the shank part of the blade through electric-discharge machining(S5), a step of forming a plurality of straight holes in the airfoil part of the blade by using the EDM super drill(S6), and a step of forming an airfoil cooling hole in the airfoil part of the blade through electric-discharge machining(S7).