Patent ID: 8210814
Filing Date: 2012-07-03
Classification: F01D,F05D,Y02T

Abstract:
1. A turbine airfoil comprising: pressure and suction sidewalls extending longitudinally in span and axially in chord between opposite leading and trailing edges and spaced transversely apart therebetween to define a plurality of flow channels extending longitudinally and separated chordally by partitions bridging said sidewalls; one of said partitions is perforate with a longitudinal row of crossover holes, each of the crossover holes extending obliquely therethrough and between one of said channels that is coupled with an inlet adapted to be connected to a source of pressurized coolant and designated as an inlet channel on one side of said perforate partition and one of said channels designated as an outlet channel on an opposite side thereof; said crossover holes are inclined longitudinally through said perforate partition counter to said longitudinal inlet channels for reversing direction of coolant channeled therethrough, wherein said crossover holes extend axially through said perforate partition along a camber line bisecting said airfoil between said leading and trailing edges; and banks of turbulators lining said pressure and suction sidewalls inside said inlet channel for introducing secondary flow in said coolant, and inclined longitudinally relative to said crossover holes for channeling locally cool coolant thereto.