| 摘要 |
A rotor blade for a gas turbine, in particular a turbojet, the blade comprising an airfoil, a platform connecting the airfoil to a blade root and having at least one stiffener extending under the downstream portion of the platform, together with means for cooling the blade by a flow of cooling fluid in ducts formed in the blade and in a cavity formed in the stiffener substantially in register with the trailing edge of the blade, and including outlet orifices facing downstream.
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