ROTOR BLADE FOR GAS TURBINE, METHOD FOR MANUFACTURING SAME, AND GAS TURBINE USING ROTOR BLADE

摘要

A rotor blade for a gas turbine, configured so that a cooling path provided within the rotor blade can be formed easily and so that the formation of the cooling path does not impair the strength and rigidity of the rotor blade. A rotor blade (41) for a gas turbine is configured in such a manner that a cooling path (410) formed within the rotor blade (41) comprises: rectilinear path-like base-side long holes (410a) extending in the longitudinal direction on the base end side of the rotor blade (41); rectilinear path-like front end-side long holes (410b) extending in the longitudinal direction on the front end side of the rotor blade (41); and communication cavity sections (410c) which are located at the connection section at which the long holes (410a) and the long holes (410b) are connected, the communication cavity sections (410c) connecting the long holes (410a, 410b) in a one-to-one correspondence and having a greater cross-sectional area than the paths of the long holes (410a, 410b). The communication cavity sections (410c) are formed so as to match the position of the platform section (413) of the rotor blade (41).