Patent ID: 7980822

Claim:
A cooling arrangement for a pressure side of an airfoil portion of a turbine engine component comprising: a pair of cooling circuits embedded within a wall forming said pressure side; said pair of cooling circuits comprising a first serpentine cooling circuit and a second non-serpentine circuit offset from said first serpentine cooling circuit; and said first serpentine cooling circuit having an inlet leg which communicates with a first inlet and which extends along an entire span of said airfoil portion for creating a flow of cooling fluid in a first spanwise direction and a second leg communicating with said inlet leg to create a flow of said cooling fluid in a second spanwise direction opposed to said first spanwise direction and an outlet leg communicating with said second leg, said cooling fluid flowing through said outlet leg in a spanwise direction opposed to said second spanwise direction and out through at least one tip hole; and said non-serpentine cooling circuit having a radially extending passageway which is not in fluid communication with said first serpentine cooling circuit and which extends over lower and upper spans of the airfoil portion, said radially extending passageway communicating with a plurality of film slots for allowing cooling fluid in said radially extending passageway to flow over an external surface the pressure side of the airfoil.