Patent ID: 8517684
Filing Date: 2013-08-27
Classification: F01D,F05D

Abstract:
1. A turbine blade for use in a gas turbine engine, the turbine blade comprising: an airfoil extending from a root and platform, the airfoil having a leading edge and a trailing edge and a pressure side wall and a suction side wall extending between the two edges; the blade including a tip section; a serpentine flow cooling circuit to produce near wall cooling of the airfoil; the serpentine flow cooling circuit comprising a first channel having a plurality of impingement cooling holes arranged along the channel in series, a second channel downstream from the first channel in the cooling flow direction, and a third channel downstream from the second channel in the cooling flow direction, the third channel having a plurality of impingement cooling holes arranged along the channel in series; and, the second channel being substantially unobstructed to the cooling air flow.