Method and apparatus for reducing turbine blade tip region temperatures

摘要

A rotor blade for a gas turbine engine including a tip region (60) that facilitates reducing operating temperatures of the rotor blade is described. The tip region includes a first tip wall (62) and a second tip wall (64) extending radially outward from a tip plate (54) of an airfoil (42). The tip walls extend from adjacent a leading edge (48) of the airfoil to connect at a trailing edge (50) of the airfoil. A portion of the second tip wall is recessed to define a tip shelf (90) that extends from the airfoil leading edge to the airfoil trailing edge.