Patent ID: 7497661

Claim:
A rotor blade for a gas turbine, the blade comprising: an airfoil having a trailing edge and a leading edge, said airfoil defining airfoil cooling fluid ducts, a blade root defining root cooling fluid ducts that are in fluid communication with said airfoil cooling fluid ducts, a platform connecting the airfoil to the blade root, at least one stiffener between said platform and said blade root and including a plane web extending from the platform from its side opposite from the airfoil and passing under the trailing edge of the airfoil, and a cooling cavity formed in a trailing edge portion of the plane web of the stiffener, said trailing edge portion being adjacent to the platform and being situated substantially in alignment with the trailing edge of the airfoil, said cavity being in fluid communication with at least one of said root cooling fluid flow ducts formed in the blade root.