Patent ID: 7988419
Filing Date: 2011-08-02
Classification: F01D,F05D

Abstract:
1. A large turbine blade comprising: a root section with a cooling air supply channel formed therein; an airfoil portion extending from the root section and having a lower span section and an upper span section; a forward flowing serpentine flow cooling circuit located in the lower span of the airfoil to provide internal cooling for the lower span of the airfoil; an aft flowing serpentine flow cooling circuit located in the upper span of the airfoil to provide internal cooling for the upper span of the airfoil; and, a last leg of the lower span serpentine flow cooling circuit and a first leg of the upper span serpentine flow cooling circuit being one long channel extending from near the root to near the tip of the airfoil and positioned along the leading edge of the airfoil.