Patent ID: 7762774

Claim:
A cooling arrangement for a tapered industrial gas turbine blade having a root/tip cross-sectional area ratio of at least 4:1, the cooling arrangement comprising: at least one serpentine cooling circuit formed in an inner radial portion of the blade said at least one serpentine cooling circuit including, a first serpentine cooling circuit in an inner radial portion of a leading edge portion of the blade, and a second serpentine cooling circuit in an inner radial portion of a trailing edge portion of the blade; and at least one single radial channel cooling circuit formed in an outer radial portion of the blade and fluidly connected to receive cooling fluid exhausted from the at least one serpentine cooling circuit, said at least one single radial channel cooling circuit including, a first single radial channel cooling circuit formed in an outer radial portion of the leading edge portion of the blade and fluidly connected to receive cooling fluid exhausted from the first serpentine cooling circuit; a second single radial channel cooling circuit formed in an outer radial portion of the trailing edge portion of the blade and fluidly connected to receive cooling fluid exhausted from the second serpentine cooling circuit.