Turbine vane with coupon having corrugated surface(s)

1. A turbine vane comprising:

two platforms;

an airfoil body positioned between the two platforms, the airfoil body including:

a leading edge extending radially between the two platforms,

a trailing edge extending radially between the two platforms, axially opposite the leading edge, and

a smooth outer surface extending between the leading edge and the trailing edge;

a cutout within at least one of the leading edge and the trailing edge, the cutout removing a predetermined area of the airfoil body; and

a coupon coupled in the cutout to replace the predetermined area of the airfoil body, the coupon including:

a first corrugated surface on at least a portion of an outer surface of the coupon, the first corrugated surface including a plurality of radially-spaced ridges and grooves, each of the plurality of radially-spaced ridges and grooves extend axially over at least a portion of the outer surface of the coupon;

a second corrugated surface on at least a portion of an inner surface of the coupon, opposite the outer surface, the second corrugated surface paralleling the first corrugated surface; and

an impingement cooling structure positioned within a coupon radially extending chamber formed in the coupon, the impingement cooling structure including:

a third corrugated surface on at least a portion of an outer surface of the impingement cooling structure, the third corrugated surface paralleling the first corrugated surface of the coupon.

2. The turbine vane of claim 1 , wherein the airfoil body includes an airfoil coolant flow passage therein, the cutout exposing the airfoil coolant flow passage, and

wherein the coupon includes a first coupon coolant flow passage configured to fluidly mate with the airfoil coolant flow passage.

3. The turbine vane of claim 2 , wherein the coupon includes a plurality of flow passages extending from an interior surface thereof to the outer surface thereof.

4. The turbine vane of claim 2 , wherein the cutout is positioned in the trailing edge, and the coupon includes a pin bank within the first coupon coolant flow passage.

5. The turbine vane of claim 2 , wherein the airfoil body includes an airfoil radially extending chamber therein and an airfoil rib partitioning the airfoil radially extending chamber to form the airfoil coolant flow passage therein, the cutout exposing the airfoil rib and the airfoil coolant flow passage, and

wherein the coupon includes a first coupon rib partitioning the coupon radially extending chamber to form the first coupon coolant flow passage.

6. The turbine vane of claim 5 , wherein the coupon includes at least one second coupon rib partitioning the coupon radially extending chamber into at least one second coupon coolant flow passage, the at least one second coupon flow passage having a different shape than the first coupon coolant flow passage.

7. The turbine vane of claim 6 , wherein the coupon further includes a pin bank within the at least one second coupon coolant flow passage.

8. The turbine vane of claim 1 , wherein the coupon includes a second corrugated surface on at least a portion of an internal surface thereof, the second corrugated surface parallel to the first corrugated surface.

9. The turbine vane of claim 1 , wherein the cutout is positioned in the trailing edge, and the coupon includes a crenulated trailing edge meshing with the first corrugated surface.

10. The turbine vane of claim 9 , wherein the coupon includes a first coupon coolant flow passage and a plurality of coolant flow passages passing from the first coupon coolant flow passage through the trailing edge of the coupon.

11. The turbine vane of claim 1 , wherein the impingement cooling structure further includes a fourth corrugated surface on at least a portion of an inner surface of the impingement cooling structure, opposite the outer surface, the fourth corrugated surface paralleling the third corrugated surface.

12. A coupon for replacing a cutout of a predetermined area in an airfoil body of a turbine vane, the airfoil body having a leading edge extending radially between two platforms of the turbine vane, a trailing edge extending radially between the two platforms and axially opposite the leading edge, and a smooth outer surface extending between the leading edge and the trailing edge, the cutout within at least one of the leading edge and the trailing edge of the airfoil body, the coupon comprising:

a first corrugated surface on at least a portion of an outer surface thereof, the first corrugated surface including a plurality of radially-spaced ridges and grooves, each of the plurality of radially-spaced ridges and grooves extend axially over at least a portion of the outer surface of the coupon; and

a second corrugated surface on at least a portion of an inner surface thereof, opposite the outer surface, the second corrugated surface paralleling the first corrugated surface; and

an impingement cooling structure positioned within a coupon radially extending chamber at least partially defined by the inner surface, the impingement cooling structure including:

a third corrugated surface on at least a portion of an outer surface of the impingement cooling structure, the third corrugated surface paralleling the first corrugated surface.

13. The coupon of claim 12 , further comprising a first coupon coolant flow passage configured to fluidly mate with an airfoil coolant flow passage in the airfoil body exposed by the cutout.

14. The coupon of claim 13 , wherein the coupon includes a pin bank within the first coupon coolant flow passage.

15. The coupon of claim 13 , wherein the coupon includes:

a first coupon rib partitioning the coupon radially extending chamber to form the first coupon coolant flow passage, and

at least one second coupon rib partitioning the coupon radially extending chamber into at least one second coupon coolant flow passage, the at least one second coupon flow passage having a different shape than the first coupon coolant flow passage.

16. The coupon of claim 15 , wherein the coupon further includes a pin bank within the at least one second coupon coolant flow passage.

17. The coupon of claim 12 , wherein the coupon includes a plurality of flow passages extending from an interior surface thereof to the outer surface thereof.

18. The coupon of claim 12 , wherein the coupon includes a second corrugated surface on at least a portion of an internal surface thereof, the second corrugated surface parallel to the first corrugated surface.

19. The coupon of claim 12 , wherein the coupon includes:

a crenulated trailing edge meshing with the first corrugated surface;

a first coupon coolant flow passage therein; and

a plurality of coolant flow passages passing from the first coupon coolant flow passage through the crenulated trailing edge of the coupon.

20. A non-transitory computer readable storage medium storing code representative of a coupon for replacing a cutout of a predetermined area in one of a leading edge or a trailing edge in an airfoil body of a turbine vane, the coupon physically generated upon execution of the code by a computerized additive manufacturing system, the code comprising:

code representing the coupon, the coupon including:

a first corrugated surface on at least a portion of an outer surface thereof, the first corrugated surface including a plurality of radially-spaced ridges and grooves, each of the plurality of radially-spaced ridges and grooves extending over a span of at least a portion of the outer surface of the coupon;

a second corrugated surface on at least a portion of an inner surface thereof, opposite the outer surface, the second corrugated surface paralleling the first corrugated surface; and

an impingement cooling structure positioned within a coupon radially extending chamber formed in the coupon, the impingement cooling structure including:

a third corrugated surface on at least a portion of an outer surface of the impingement cooling structure, the third corrugated surface paralleling the first corrugated surface of the coupon.