Trip strip restagger

1. A structure for creating a core for gas turbine engine component comprising:

a body with a curved surface defining a turn passage, wherein the curved surface comprises an inner wall portion and wherein the body includes an outer wall portion spaced apart from the inner wall portion by a wall surface, and wherein a terminal end of the inner wall portion includes the curved surface; and

a plurality of protrusions formed within the wall surface of the turn passage, wherein the plurality of protrusions are configured to extend in a radial direction relative to the curved surface, and wherein each protrusion is defined by a length extending from a first end facing the inner wall portion to a second end facing the outer wall portion, and wherein first ends of at least two adjacent protrusions are connected to each other via a protrusion curved surface.

2. The structure for creating the core according to claim 1 wherein the curved surface protrudes outwardly from the wall surface.

3. The structure for creating the core according to claim 2 wherein the protrusions are spaced apart from each other.

4. The structure for creating the core according to claim 2 wherein the protrusions are defined by different lengths.

5. The structure for creating the core according to claim 2 wherein each of the first ends is spaced apart from the curved surface.

6. The structure for creating the core according to claim 5 wherein each of the second ends of the protrusions extend to contact the outer wall portion.

7. The structure for creating the core according to claim 2 wherein the turn passage is defined by a first linear portion, a second linear portion spaced apart from and parallel to the first linear portion, and a third portion that transitions from the first linear portion to the second linear portion about the curved surface.

8. The structure for creating the core according to claim 7 wherein the protrusions are only positioned in the third portion.

9. The structure for creating the core according to claim 7 wherein longer protrusions are positioned between shorter protrusions.

10. The structure for creating the core according to claim 1 wherein the gas turbine engine component comprises one of an airfoil, a blade, a vane, a BOAS, or a combustor panel.

11. The structure for creating the core according to claim 1 wherein each of the first ends of the protrusions do not contact the inner wall portion.

12. The structure for creating the core according to claim 1 wherein the lengths of the protrusions vary.

13. The structure for creating the core according to claim 1 wherein the turn passage is defined by a first linear portion, a second linear portion spaced apart from and generally parallel to the first linear portion, and a third portion that transitions from the first linear portion to the second linear portion about the curved surface.

14. A gas turbine engine component comprising:

a body including an internal turn passage extending about a curved surface, wherein the curved surface comprises an inner wall portion and wherein the body includes an outer wall portion spaced apart from the inner wall portion by a wall surface, and wherein a terminal end of the inner wall portion includes the curved surface; and

a plurality of trip strips formed within the wall surface of the turn passage, wherein the plurality of trip strips are configured to extend radially relative to the curved surface, and wherein each trip strip is defined by a length extending from a first end facing the inner wall portion to a second end facing the outer wall portion, and wherein first ends of at least two adjacent trip strips are connected to each other via a protrusion curved surface.

15. The gas turbine engine component according to claim 14 wherein the trip strips are defined by different lengths.

16. The gas turbine engine component according to claim 14 wherein each of the second ends of the trip strips contact the outer wall portion and wherein each of the first ends of the trip strips are spaced apart from the inner wall portion.

17. The gas turbine engine component according to claim 14 wherein the turn passage is defined by a first linear portion, a second linear portion spaced apart from and parallel to the first linear portion, and a third portion that transitions from the first linear portion to the second linear portion about the curved surface, and wherein the trip strips are only positioned in the third portion.

18. A method of manufacturing a gas turbine engine component comprising:

providing a body including an internal turn passage extending about a curved surface, wherein the curved surface comprises an inner wall portion and wherein the body includes an outer wall portion spaced apart from the inner wall portion by a wall surface, and wherein a terminal end of the inner wall portion includes the curved surface;

forming a plurality of trip strips within the wall surface of the turn passage, wherein the plurality of trip strips are configured to extend radially relative to the curved surface, and wherein each trip strip is defined by a length extending from a first end facing the inner wall portion to a second end facing the outer wall portion, and wherein first ends of at least two adjacent trip strips are connected to each other via a protrusion curved surface; and

forming the trip strips using one of a casting, EDM, laser, or additive manufacturing method.

19. The method according to claim 18 wherein each of the second ends of the trip strips contact the outer wall portion and wherein each of the first ends of the trip strips are spaced apart from the inner wall portion.

20. The method according to claim 18 wherein the turn passage is defined by a first linear portion, a second linear portion spaced apart from and parallel to the first linear portion, and a third portion that transitions from the first linear portion to the second linear portion about the curved surface, and wherein the trip strips are only positioned in the third portion.