Methods and apparatus for cooling gas turbine rotor blades

摘要

A rotor blade (40) for a gas turbine includes a platform (62) including a radially outer surface (144) and a radially inner surface (142). The platform radially inner surface includes an undercut (140) and a purge slot (160) formed therein. The purge slot channels cooling air downstream to facilitate cooling a portion of the platform during engine operation. An airfoil (60) extends radially from the platform radially outer surface. A shank (64) extends radially from the platform radially inner surface, and a dovetail (66) extends from the shank for coupling the rotor blade within the gas turbine engine.