FILM SHAPE STRUCTURE OF COOLING HOLE FOR COOLING GAS TURBINE BLADES

摘要

The present invention relates to a film shape structure of a cooling hole for cooling gas turbine blades, wherein the shape of a film cooling hole which is used for the purpose of cooling gas turbine blades is specifically set so as to more widely and effectively distribute cooling fluid throughout a cooling surface such that remarkably improved cooling efficiency can be obtained when compared with existing hole structures. The present invention relates to the film shape structure of a film cooling hole for cooling gas turbine blades, comprising: a cylindrical part having a predetermined cross-section area, an expansion part connected to the upper end of the cylindrical part and having a cross-section area which gradually increases, and a protrusion part protruding in the center portion of a hole outlet so as to protrude to the expansion part.