GAS TURBINE ROTOR BLADE, AND GAS TURBINE

摘要

Provided is a cooling structure for a gas turbine rotor blade being capable of effectively using the cooling air which was used for convection cooling a fillet part as the cooling air for cooling the interior of a blade body without drilling holes on the outer surface of a platform or on the blade surface having large thermal stress and without discharging the aforementioned cooling air into combustion gas from the cooling holes in the vicinity of the fillet part. A gas turbine rotor blade formed from: a platform; a blade body having a cooling path containing a serpentine cooling path; a fillet part disposed on the connecting surface of the blade body and the platform; and a base part having a cooling path which is in communication with the serpentine cooling path. The aforementioned cooling paths are provided with a bypass path connected to the low pressure part of the cooling paths by branching from the high pressure part of the cooling paths and by passing through the vicinity of the interior of the fillet part.