Patent ID: 8628298

Claim:
A turbine rotor blade for an industrial gas turbine engine, the turbine rotor blade comprising: an airfoil section with a lower span section and an upper span section; a common cooling air supply channel extending from a platform section to a blade tip section of the airfoil; a first three-pass forward flowing serpentine flow cooling circuit located in the lower span section and having a second leg connected to the common cooling air supply channel and a third leg located along a leading edge of the airfoil; a second three-pass forward flowing serpentine flow cooling circuit located in the upper span section and having a second leg connected to the common cooling air supply channel and a third leg located along a leading edge of the airfoil; a first five-pass aft flowing serpentine flow cooling circuit located in the lower span section and having a second leg connected to the common cooling air supply channel and a fifth leg located adjacent to a trailing edge of the airfoil; a second five-pass aft flowing serpentine flow cooling circuit located in the upper span section and having a second leg connected to the common cooling air supply channel and a fifth leg located adjacent to a trailing edge of the airfoil; and, the common cooling air supply channel forms the first leg for each of the serpentine flow cooling circuits.