| 摘要 |
PROBLEM TO BE SOLVED: To provide a method and a device for cooling a gas turbine engine rotor blade. SOLUTION: This method for manufacturing the turbine rotor blade 50 comprises a step for casting the turbine rotor blade including a dovetail 66, a platform 62 having an outer surface 102, an inner surface 104, and a cast-in plenum 100 formed between the outer surface and the inner surface, and a blade-shaped part 60 and a step for forming a plurality of holes 160 for cooling the outer surface of the platform between the inner surface and the outer surface of the platform. COPYRIGHT: (C)2006,JPO&NCIPI
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