General Electric Company
TURBOMACHINE ROTOR BLADE WITH A COOLING CIRCUIT HAVING AN OFFSET RIB

Abstract:

A rotor blade for a turbomachine is provided. The rotor blade includes a platform, an airfoil extending from the platform, and a cooling circuit extending within the platform and the airfoil. The cooling circuit includes a plurality of cooling passages defined by a plurality of ribs. The plurality of ribs includes an offset rib.