Patent ID: 7641445
Filing Date: 2010-01-05
Classification: F01D,F05D

Abstract:
1. A rotor blade for use in a gas turbine engine, the rotor blade comprising: a root portion having a cooling air supply passage; an airfoil portion extending from the root portion to a blade tip; a multiple pass serpentine flow cooling circuit formed within the airfoil portion, the serpentine flow cooling circuit including a first leg and a last leg, and a middle leg positioned in the serpentine flow direction between the first and the last legs, the middle leg having an upper portion formed of at least a single channel with trip strips located within the single channel and a lower portion having a plurality of cooling channels in fluid communication with the at least one single channel; and, the cooling channels in the lower portion include a plurality of near wall cooling channels extending along the pressure side of the blade and a plurality of near wall cooling channels extending along the suction side of the blade.