| 摘要 |
A turbine rotor blade for a gas turbine engine including an airfoil and dovetail for mounting the airfoil along a radial axis to a rotor disk inboard of a turbine shroud, the airfoil comprising: a pressure sidewall and a suction sidewall that join together at a leading edge and a trailing edge, the pressure sidewall and suction sidewall extending from a root to a tip plate; a pressure tip wall that extends radially outwardly from the tip plate, traversing from the leading edge to the trailing edge such that the pressure tip wall resides approximately adjacent to the termination of the pressure sidewall; a suction tip wall that extends radially outwardly from the tip plate, traversing from the leading edge to the trailing edge such that the suction tip wall resides approximately adjacent to the termination of the suction sidewall; and one or more tip ribs that extend substantially between the pressure tip wall and the suction tip wall.
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