| 摘要 |
A rotor blade (40) 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 notch (80) is defined between the first and second tip walls at the airfoil leading edge. At least a portion of the second tip wall is recessed to define a tip shelf (90).
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