| 摘要 |
PROBLEM TO BE SOLVED: To provide a rotor blade 52 for a gas turbine engine 10. SOLUTION: The rotor blade comprises a platform 62, an airfoil profile 60 extended outward in the radial direction from the platform, a shank 64 extended inward in the radial direction from the platform, a dovetail 66 extended form the shank, and a cooling circuit 13 extended through a part of the shank. The cooling circuit supplies cooling air for impingement-cooling in, at least, one part of the rotor blade, and the purged air flows in the downstream of the rotor blade toward inside a cavity 110 defined inside the gas turbine engine. COPYRIGHT: (C)2005,JPO&NCIPI
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