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An airfoil in a gas turbine engine includes an outer wall, a cooling fluid cavity, and a plurality of cooling fluid passages. The outer wall has a leading edge, a trailing edge, a pressure side, a suction side, and radially inner and outer ends. The cooling fluid cavity is defined in the outer wall,

An airfoil in a gas turbine engine includes an outer wall, a cooling fluid cavity, and a plurality of cooling fluid passages. The outer wall has a leading edge, a trailing edge, a pressure side, a suction side, and radially inner and outer ends. The cooling fluid cavity is defined in the outer wall, extends generally radially between the inner and outer ends of the outer wall, and receives cooling fluid for cooling the outer wall. The cooling fluid passages are in fluid communication with the cooling fluid cavity and include zigzagged passages that include alternating angled sections, each section having both a radial component and a chordal component. The cooling fluid passages extend from the cooling fluid cavity toward the trailing edge of the outer wall and receive cooling fluid from the cooling fluid cavity for cooling the outer wall near the trailing edge.

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1. 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 def

1. 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; anda plurality of cooling fluid passages in fluid communication with the cooling fluid cavity, the cooling fluid passages comprising zigzagged passages that include 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, wherein the cooling fluid passages are gradually tapered in a circumferential direction as the cooling fluid passages extend from the cooling fluid cavity toward the trailing edge of the outer wall, the circumferential direction defined between the pressure side and the suction side of the outer wall, and wherein radial heights of the cooling fluid passages are greater than radial spaces between radially adjacent cooling fluid passages. 2. The airfoil according to claim 1, further comprising a plurality of outlet passages located in the outer wall at the trailing edge, the outlet passages receiving cooling fluid from the cooling fluid passages and discharging the cooling fluid from the airfoil. 3. The airfoil according to claim 2, further comprising a cooling fluid channel located between the cooling fluid passages and the outlet passages and extending generally radially between the inner end and the outer end of the outer wall, the cooling fluid channel receiving cooling fluid from the cooling fluid passages and delivering the cooling fluid to the cooling fluid outlet passages. 4. The airfoil according to claim 1, wherein the chordal component is substantially equal to the radial component for each section. 5. The airfoil according to claim 1, wherein the alternating angled sections of each cooling fluid passage comprise at least a first section angled radially outwardly in a downstream direction and at least a second section extending from the first section and angled radially inwardly in the downstream direction. 6. The airfoil according to claim 5, wherein the angle of the second section is substantially equal and opposite to the angle of the first section. 7. The airfoil according to claim 5, wherein the angle of the first section is within a range of about (25) to about (60) degrees, and the angle of the second section is with a range about (−25) to about (−60) degrees. 8. The airfoil according to claim 1, wherein the respective sections of radially adjacent cooling fluid passages are nested together in close proximity to each other. 9. The airfoil according to claim 8, wherein the cooling fluid passages are configured such that at least one of: radial peaks of at least some of the cooling fluid passages are located at a radial location at or radially outwardly from a radial location of at least one of an entrance portion and an exit portion of a radially outwardly adjacent cooling fluid passage; andradial valleys of at least some of the cooling fluid passages are located at a radial location at or radially inwardly from a radial location of at least one of an entrance portion and an exit portion of a radially inwardly adjacent cooling fluid passage. 10. The airfoil according to claim 1, wherein turns between adjacent sections of each cooling passage comprise continuously curved walls. 11. The airfoil according to claim 1, wherein the cooling fluid passages are configured such that cooling fluid flowing through each cooling fluid passage does not mix with cooling fluid flowing through the other cooling fluid passages until the cooling fluid exits the cooling fluid passages. 12. The airfoil according to claim 1, further comprising a plurality of turbulating features provided within the cooling fluid passages, the turbulating features effecting a turbulated flow of cooling fluid through the cooling fluid passages, wherein the turbulating features are arranged generally perpendicular to an extension direction of the alternating sections of the cooling fluid passages. 13. The airfoil according to claim 1, wherein the cooling fluid passages are cast integrally with the outer wall using a sacrificial ceramic core. 14. 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, the cooling fluid cavity receiving cooling fluid for cooling the outer wall; anda plurality of cooling fluid passages including alternating angled sections, each section extending radially and chordally toward the trailing edge of the outer wall, the cooling fluid passages receiving cooling fluid from the cooling fluid cavity for cooling the outer wall near the trailing edge, wherein the cooling fluid passages are configured such that respective sections of radially adjacent cooling fluid passages are nested together in close proximity to each; andwherein radial heights of the cooling fluid passages remain substantially constant throughout the entire chordal lengths of the cooling fluid passages, and wherein radial heights of the cooling fluid passages are greater than radial spaces between radially adjacent cooling fluid passages. 15. The airfoil according to claim 14, further comprising: a cooling fluid channel located downstream from the cooling fluid passages, the cooling fluid channel receiving cooling fluid from the cooling fluid passages; anda plurality of outlet passages located in the outer wall at the trailing edge, the outlet passages receiving cooling fluid from the cooling fluid channel and discharging the cooling fluid from the airfoil. 16. The airfoil according to claim 14, wherein the alternating angled sections of each cooling fluid passage comprise at least a first section angled radially outwardly in a downstream direction and at least a second section extending from the first section and angled radially inwardly in the downstream direction, wherein the angle of the first section is within a range of about (25) to about (60) degrees, and the angle of the second section is with a range about (−25) to about (−60) degrees. 17. The airfoil according to claim 14, wherein the cooling fluid passages are configured such that at least one of: radial peaks of at least some of the cooling fluid passages are located at a radial location at or radially outwardly from a radial location of at least one of an entrance portion and an exit portion of a radially outwardly adjacent cooling fluid passage; andradial valleys of at least some of the cooling fluid passages are located at a radial location at or radially inwardly from a radial location of at least one of an entrance portion and an exit portion of a radially inwardly adjacent cooling fluid passage. 18. The airfoil according to claim 14, wherein turns between adjacent sections of each cooling passage comprise continuously curved walls. 19. The airfoil according to claim 14, wherein the cooling fluid passages are gradually tapered in a circumferential direction as the cooling fluid passages extend from the cooling fluid cavity toward the trailing edge of the outer wall, the circumferential direction defined between the pressure side and the suction side of the outer wall. 20. The airfoil according to claim 14, further comprising a plurality of turbulating features provided within the cooling fluid passages, the turbulating features effecting a turbulated flow of cooling fluid through the cooling fluid passages, wherein the turbulating features are arranged generally perpendicular to an extension direction of the alternating sections of the cooling fluid passages.