Patent attributes
A ceramic core used to make a first or second stage turbine blade in an industrial gas turbine engine. The ceramic core includes a serpentine flow forming pierce with a trailing edge cooling supply channel forming piece on the trailing edge end. Three rows of metering holes are formed by a core piece in which a continuous flow channel piece on the tip portion and the root portion of the blade support the core piece that forms the metering holes and impingement cavity pieces such that the ceramic core is rigid and strong to prevent shear force and local bending of the core during casting will not break the core. A first and a second stage turbine blade is formed from the ceramic core and includes a forward flowing serpentine flow circuit for the first stage blade with the first channel of the serpentine flow circuit forming the trailing edge supply channel. A second stage blade includes an aft flowing serpentine flow circuit with the last channel forming the trailing edge supply channel. The three rows of metering holes allow for a gradual pressure drop from the high pressure trailing edge cooling supply channel and out the discharge holes or ducts along the edge of the blade.