Turbine airfoil with trailing edge cooling featuring axial partition walls

1. An airfoil for a turbine engine comprising:

an outer wall delimiting an airfoil interior, the outer wall extending span-wise in a radial direction of the turbine engine and being formed by a pressure side and a suction side joined at a leading edge and at a trailing edge, wherein a chordal axis is defined extending centrally between the pressure and suction sides;

a plurality of pins positioned in the airfoil interior toward the trailing edge, each extending from the pressure side to the suction side and further being elongated in a radial direction, the plurality of pins being arranged in multiple radial rows spaced along the chordal axis, with the pins in each row being interspaced to define coolant passages therebetween; and

a row of radially spaced apart partition walls positioned aft of a last row of pins, wherein each partition wall extends from the pressure side to the suction side and is elongated in a generally axial direction, extending along the chordal axis to terminate at the trailing edge, whereby axially extending coolant exit slots are defined in the interspaces between adjacent partition walls that direct coolant exiting the last row of pins to be discharged from the airfoil into a hot gas path,

wherein each elongated pin of the plurality of pins has a length dimension parallel to the radial direction that is greater than a width dimension parallel to the chordal axis,

wherein each of the partition walls occupies a radial position that is aligned with a mid portion of a respective pin in the last row of pins, and

wherein one or more turbulators are positioned in each exit slot at the pressure side and the suction side respectively.

2. The airfoil according to claim 1 , wherein the pins in adjacent rows are staggered in the radial direction.

3. The airfoil according to claim 1 , wherein each elongated pin of the plurality of pins is made up of first and second sides generally parallel to the radial direction, and third and fourth sides extending transverse to the radial direction.

4. The airfoil according to claim 3 , wherein the third and fourth sides are convex.

5. The airfoil according to claim 1 , wherein along the radial direction, a width of each exit slot is greater than a width of each partition wall.

6. The airfoil according to claim 1 , wherein the partition walls occupy radial positions that are staggered with respect to coolant passages in the last row of pins.

7. The airfoil according to claim 1 , wherein the turbulators at the pressure side and suction side are offset along the chordal axis.

8. The airfoil according to claim 1 , wherein the turbulators at the pressure side and suction side overlap in a direction transverse to the chordal axis.

9. The airfoil according to claim 1 , wherein the turbulators are angled to guide coolant flow in the exit slot toward the adjacent partition walls.

10. The airfoil according to claim 9 , wherein each of the pressure side and the suction side has at least one turbulator angled toward a radially outer adjacent partition wall and at least one turbulator angled toward a radially inner adjacent partition wall.

11. The airfoil according to claim 10 , wherein turbulators angled toward the radially outer adjacent partition wall alternate with turbulators angled toward the radially inner adjacent partition wall along the chordal axis.

12. An airfoil for a turbine engine comprising:

an outer wall delimiting an airfoil interior, the outer wall extending span-wise in a radial direction of the turbine engine and being formed by a pressure side and a suction side joined at a leading edge and at a trailing edge, wherein a chordal axis is defined extending centrally between the pressure and suction sides;

a plurality of pins positioned in the airfoil interior toward the trailing edge, each extending from the pressure side to the suction side and further being elongated in a radial direction, the plurality of pins being arranged in multiple radial rows spaced along the chordal axis, with the pins in each row being interspaced to define coolant passages therebetween and the pins in adjacent rows being staggered along the radial direction;

a row of radially spaced apart partition walls positioned aft of a last row of pins, wherein each partition wall extends from the pressure side to the suction side and is elongated in a generally axial direction, extending along the chordal axis to terminate at the trailing edge, whereby axially extending coolant exit slots are defined in the interspaces between adjacent partition walls that direct coolant exiting the last row of pins to be discharged from the airfoil into a hot gas path; and

a plurality of turbulators positioned in each exit slot, the turbulators being angled to guide coolant flow in the exit slot toward the adjacent partition walls,

wherein each elongated pin of the plurality of pins has a length dimension parallel to the radial direction that is greater than a width dimension parallel to the chordal axis, and

wherein each of the partition walls occupies a radial position that is aligned with a mid portion of a respective pin in the last row of pins.

13. The airfoil according to claim 12 , wherein along the radial direction, a width of each exit slot is greater than a width of each partition wall.

14. The airfoil according to claim 12 , wherein the partition walls occupy radial positions that are staggered with respect to coolant passages in the last row of pins.

15. The airfoil according to claim 12 , wherein each of the pressure side and the suction side has at least one turbulator angled toward a radially outer adjacent partition wall and at least one turbulator angled toward a radially inner adjacent partition wall.

16. The airfoil according to claim 15 , wherein turbulators angled toward the radially outer adjacent partition wall alternate with turbulators angled toward the radially inner adjacent partition wall along the chordal axis.