Blade outer air seal with flow guide manifold

1. A seal assembly comprising:

a seal arc segment defining radially inner and outer sides, the radially outer side including radially-extending sidewalls and a radially inner surface joining the radially-extending sidewalls, the radially-extending sidewalls and the radially inner surface defining a pocket;

a manifold disposed at least partially in the pocket, the manifold subdividing the pocket such that there is a manifold chamber bounded by the manifold and the radially inner surface, the manifold including at least one inlet and a plurality of outlets;

a seal disposed between the radially-extending sidewalls and the manifold, wherein the seal is contiguous with the radially inner surface.

2. The seal assembly as recited in claim 1 , wherein the manifold subdivides the pocket into the manifold chamber and a manifold exhaust chamber that is radially outwards of the manifold chamber.

3. The seal assembly as recited in claim 2 , wherein the plurality of outlets open into the manifold exhaust chamber.

4. The seal assembly as recited in claim 2 , wherein the manifold exhaust chamber is bounded, exclusive of the radially inner surface, by the manifold and the radially-extending sidewalls.

5. The seal assembly as recited in claim 1 , wherein the at least one inlet is flared.

6. The seal assembly as recited in claim 1 , wherein the manifold includes a peripheral seal groove, and the seal is partially disposed in the peripheral seal groove.

7. The seal assembly as recited in claim 1 , wherein the manifold includes at least one flow guide that protrudes into the manifold chamber.

8. The seal assembly as recited in claim 1 , wherein the seal arc segment is formed of a ceramic material and the manifold is formed of a metallic alloy.

9. The seal assembly as recited in claim 1 , wherein the manifold is non-destructively removable from the pocket and the seal arc segment.

10. A seal assembly comprising:

a seal arc segment defining radially inner and outer sides, the radially outer side including radially-extending sidewalls and a radially inner surface joining the radially-extending sidewalls, the radially-extending sidewalls and the radially inner surface defining a pocket;

a manifold disposed at least partially in the pocket, the manifold subdividing the pocket such that there is a manifold chamber bounded by the manifold and the radially inner surface, the manifold including at least one inlet and a plurality of outlets, wherein the manifold subdivides the pocket into the manifold chamber and a manifold exhaust chamber that is radially outwards of the manifold chamber and the manifold exhaust chamber is bounded, exclusive of the radially inner surface, by the manifold and the radially-extending sidewalls; and

a heat shield that lines the radially-extending sidewalls of the manifold exhaust chamber.

11. A gas turbine engine comprising:

a rotor section including a rotor having a plurality of blades and at least one annular seal system circumscribing the rotor, the annular seal system comprising:

a plurality of seal arc segments and a corresponding plurality of manifolds arranged with the seal arc segments, each of the seal arc segments defining radially inner and outer sides, the radially outer side including radially-extending sidewalls and a radially inner surface joining the radially-extending sidewalls, the radially-extending sidewalls and the radially inner surface defining a pocket,

the corresponding manifold being disposed at least partially in the pocket, the manifold subdividing the pocket such that there is a manifold chamber bounded by the manifold and the radially inner surface, the manifold including at least one inlet and a plurality of outlets, wherein the manifold subdivides the pocket into the manifold chamber and a manifold exhaust chamber that is radially outwards of the manifold chamber, and the plurality of outlets open into the manifold exhaust chamber, and

a heat shield that lines the radially-extending sidewalls of the manifold exhaust chamber.

12. The gas turbine engine as recited in claim 11 , further comprising a seal disposed between the radially-extending sidewalls and the manifold.

13. The gas turbine engine as recited in claim 11 , wherein the seal arc segment is formed of a ceramic material and the manifold is formed of a metallic alloy.

14. The gas turbine engine as recited in claim 11 , wherein the manifold is non-destructively removable from the pocket and the seal arc segment.

15. A method of assembling a blade outer air seal, the method comprising:

providing a seal arc segment that defines radially inner and outer sides, the radially outer side includes radially-extending sidewalls and a radially inner surface joins the radially-extending sidewalls, the radially-extending sidewalls and the radially inner surface define a pocket; and

inserting a manifold at least partially in the pocket, the manifold subdivides the pocket such that there is a manifold chamber bounded by the manifold and the radially inner surface, the manifold includes at least one inlet and a plurality of outlets, with a seal disposed between the radially-extending sidewalls and the manifold, wherein the seal is contiguous with the radially inner surface.

16. The method as recited in claim 15 , further comprising, prior to the inserting, removing the manifold from another, different seal arc segment.