GAS TURBINE COOLED ROTOR BLADE Russian patent published in 2008 - IPC F01D5/18 

FIELD: engines and pumps.

SUBSTANCE: gas turbine cooled rotor blade is furnished with a butt and a wing, plate deflectors attached on the wing inner surfaces and forming, inside the rotor blade, a lengthwise channel carrying cooling air from the butt to the wing end face and communicating, along the wing front edge, with a set of crosswise similar-purpose channels. The latter are formed by the surfaces of plate deflector and wing and are directed from the wing front edge to the rear one, and communicate, in their turn, with a set of holes in the said wing arranged on rear edge section. The blade is made up of interconnected sections, one of them being a basic one contains a butt and one of the wing lateral sides including its front and rear edges, as well as the wing opposite lateral side surfaces parts adjoining to it to form an opening of the wing opposite lateral side. The second section, a bolt-on one, closing the wing outer surface outline is attached to the basic section all along the opening periphery. The plate deflector represents deflector elements fastened on the said blade wing basic and bolt-on sections and furnished with a set of ribs on their surfaces coupled, by their end faces, with the blade wing to form crosswise channel lateral walls. Invention allows increasing the cooling efficiency and, at the same time, a notably increase in gas temperature in operating conditions.

EFFECT: increasing the cooling efficiency and a notable increase in gas temperature in operating conditions.

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