Coolable rotor blade for a gas turbine engine

摘要

A rotor blade (40) for a gas turbine engine, including a platform (62) which comprises a radially outer surface (152), a radially inner surface, and a recessed area extending at least partially therebetween. An airfoil (60) extends radially outward from the platform, the airfoil including a first sidewall (70) and a second sidewall (72) connected together along a leading edge (74) and a trailing edge (76). A shank (64) extends radially inward from the platform including a dovetail (66) extending from the shank. An internal cavity is defined at least partially by the shank, the cavity provides cooling air for impingement cooling at least a portion of the platform radially inner surface; and a cooling circuit extends through a portion (160) of the shank for channeling cooling air through the platform recessed area during engine operation to facilitate reducing stresses induced to at least a portion of the airfoil trailing edge.