| 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 rotor blade 50 comprises a step for casting the turbine rotor blade including a shank 64 and a platform 62 having an upper face 172 and a lower face 182 and a step for connecting a first constituent element with the rotor blade to form a first substantially hollow plenum 180 between the shank and the lower face of the platform. COPYRIGHT: (C)2006,JPO&NCIPI |
