| 摘要 |
An airfoil for a gas turbine engine includes a leading edge, a trailing edge, a tip plate, a first sidewall, and a second sidewall. The first sidewall extends in radial span between an airfoil root and the tip plate. Furthermore, the first sidewall defines a pressure side of the airfoil. The second sidewall is connected to the first sidewall at the leading and trailing edges, and extends in radial span between the airfoil root and the tip plate. The second sidewall defines a suction side of the airfoil. The tip plate includes at least one groove that extends substantially between the first and second sidewalls.
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