A GAS TURBINE BLADE AND METHOD FOR FORMING AN INTERNAL COOLING PASSAGE THEREOF

摘要

PURPOSE: A gas turbine blade and a method for forming an internal cooling passage thereof are provided to improve the overall cooling performance because a spiral rib is formed in the internal cooling passage to create vortex. CONSTITUTION: A gas turbine blade(100) comprises an internal cooling passage(110) which receives cooling liquid. The internal cooling passage has a spiral rib(120) which is formed through ECM(Electro Chemical Machining).