Patent ID: 8882448

Claim:
An airfoil in a gas turbine engine comprising: an outer wall including a leading edge, a trailing edge, a pressure side, a suction side, a radially inner end, and a radially outer end, wherein a chordal direction is defined between the leading edge and the trailing edge; a cooling fluid cavity defined in the outer wall and extending generally radially between the inner end and the outer end of the outer wall, the cooling fluid cavity receiving cooling fluid for cooling the outer wall; a plurality of cooling fluid passages in fluid communication with the cooling fluid cavity, the cooling fluid passages comprising alternating angled sections, each section having both a radial component and a chordal component, the cooling fluid passages extending from the cooling fluid cavity toward the trailing edge of the outer wall and receiving cooling fluid from the cooling fluid cavity for cooling the outer wall near the trailing edge; and a plurality of radial passageways interconnecting radially adjacent cooling fluid passages, wherein the radial passageways are formed between radial peaks and radial valleys of respective radially adjacent cooling fluid passages.