BOAS carrier with cooling supply

1. A blade outer air seal assembly, comprising:

a support structure;

a blade outer air seal having a plurality of seal segments arranged circumferentially about an axis and mounted in the support structure by a carrier, wherein the seal segment has first and second walls extending from an inner platform and joined at an outer wall to form a circumferentially extending passage; and

a coverplate arranged between the carrier and at least one of the plurality of seal segments, wherein at least a portion of the carrier and the coverplate are arranged within the circumferentially extending passage of the seal segment, the coverplate forming a first passage between the coverplate and the carrier and a second passage between the coverplate and the seal segment, wherein the carrier has a channel in a radially inner surface, the channel forming the first passage, wherein the channel is formed in a recess, the recess extends a distance in a circumferential direction and the coverplate has a width in the circumferential direction that is smaller than the distance.

2. The blade outer air seal assembly of claim 1 , wherein the coverplate is welded to the carrier.

3. The blade outer air seal assembly of claim 1 , wherein the first passage has a first height and the second passage has a second height, and wherein the first height is the same or larger than the second height.

4. The blade outer air seal assembly of claim 3 , wherein the first height is between about 0.030 and 0.100 inches (0.762-2.54 mm).

5. The blade outer air seal assembly of claim 1 , wherein the first passage extends generally in the circumferential direction.

6. The blade outer air seal assembly of claim 1 , wherein a hole extends radially through the carrier.

7. The blade outer air seal assembly of claim 6 , wherein a cooling path is defined through the hole, along the first passage, along the second passage, and through a film cooling array on the seal segment.

8. The blade outer air seal assembly of claim 6 , wherein the hole is centered circumferentially on the carrier.

9. The blade outer air seal assembly of claim 6 , wherein the hole is centered axially on the carrier.

10. The blade outer air seal assembly of claim 1 , wherein the carrier has first and second hooks that form a dovetail shape for engagement with the support structure, and an axial passage is formed between the first and second hooks.

11. The blade outer air seal assembly of claim 10 , wherein the axial passage is in fluid communication with a hole in the carrier.

12. The blade outer air seal assembly of claim 1 , wherein the blade outer air seal is a ceramic matrix composite material.

13. The blade outer air seal assembly of claim 12 , wherein the carrier is a metallic material and the coverplate is a metallic material.

14. The blade outer air seal assembly of claim 1 , wherein the carrier is a metallic material.

15. The blade outer air seal assembly of claim 1 , wherein the coverplate is a metallic material.

16. A turbine section for a gas turbine engine, comprising:

a turbine blade extending radially outwardly to a radially outer tip and for rotation about an axis of rotation;

a blade outer air seal having a plurality of seal segments arranged circumferentially about the axis of rotation, each of the segments mounted in a support structure radially outward of the outer tip via a carrier, wherein the plurality of seal segments comprises a first seal segment and a second seal segment adjacent the first seal segment, wherein each of the plurality of seal segments has a first wall and a second wall extending from an inner platform and joined at an outer wall to form a circumferentially extending passage;

wherein the carrier has a plurality of carrier segments, and a coverplate arranged at a radially inward portion of each of the plurality of carrier segments, at least a portion of the carrier and the coverplate are arranged within the circumferentially extending passage, and one of the coverplates is arranged partially within the circumferentially extending passage of the first seal segment and partially within the circumferentially extending passage of the second seal segment, each coverplate forming a first passage between the coverplate and the carrier and a second passage between the coverplate and a seal segment, wherein a cooling path is defined through a hole in the carrier, circumferentially along the first passage, along the second passage, and through a film cooling array on the seal segment.

17. The turbine section of claim 16 , wherein the blade outer air seal is a ceramic matrix composite material, the carrier is a metallic material, and the coverplate is a metallic material.