Patent ID: 8882461

Claim:
An airfoil for a gas turbine engine, comprising: a pressure side wall having a pressure side trailing edge; a suction side wall coupled to the pressure side wall at a leading edge and having a suction side trailing edge, the suction side trailing edge and the pressure side trailing edge forming an airfoil trailing edge such that the airfoil extends in a chordwise direction between the leading edge and the airfoil trailing edge; an internal cavity defined between the pressure side wall and the suction side wall for receiving cooling air; and a cooling arrangement within the internal cavity, the cooling arrangement comprising: a first land extending in a circumferential direction between the suction side wall and the pressure side wall and in the chordwise direction from a first upstream end forward of the pressure side trailing edge to a first downstream end aft of the pressure side trailing edge, a second land extending in the circumferential direction between the suction side wall and the pressure side wall and in the chordwise direction from a second upstream end forward of the pressure side trailing edge to a second downstream end aft of the pressure side trailing edge, the first land and second land defining a first slot configured to direct the cooling air out of the internal cavity, at least one of a first divider positioned radially in between the first land and the second land to define a first passageway of the first slot and a second passageway of the first slot, wherein the first divider extends in the chordwise direction from a first end to a second end, the second end being positioned forward of the pressure side trailing edge relative to the chordwise direction, a first pin positioned upstream of the first divider and indexed to the first passageway, and a second pin positioned upstream of the first divider and indexed to the second passageway.