Turbine shroud having ceramic matrix composite component mounted with cooled pin

1. A turbine shroud assembly adapted for use in a gas turbine engine, the turbine shroud assembly comprising

a carrier comprising metallic materials and arranged to extend circumferentially at least partway about an axis, the carrier formed to include a feed passageway configured to conduct cooling air through a portion of the carrier,

a blade track segment comprising ceramic matrix composite materials, the blade track segment formed to include a runner shaped to extend circumferentially partway around the axis, a first mount post that extends radially outward from the runner, and a second mount post that extends radially outward from the runner, the second mount post spaced apart axially from the first mount post to define a channel therebetween, and

an intermediate carrier configured to couple the blade track segment to the carrier, the intermediate carrier including an intermediate carrier body arranged axially between the first mount post and the second mount post, at least one pin that extends axially into the first mount post, the intermediate carrier body, and the second mount post to couple the intermediate carrier body to the blade track segment, and at least one retainer that extends radially outward from the intermediate carrier body through the carrier to couple the intermediate carrier and the blade track segment with the carrier,

wherein the at least one pin is formed to include a cooling passageway that extends axially through the at least one pin and aligns with the feed passageway of the carrier such that cooling air is configured to be conducted from the feed passageway through the at least one pin to cool the at least one pin.

2. The turbine shroud assembly of claim 1 , wherein the carrier includes an outer wall that extends circumferentially at least partway about the axis, a first radial wall that extends radially inward from the outer wall, and a second radial wall that extends radially inward from the outer wall, the second radial wall is spaced apart from the first radial wall to define an attachment-receiving space therebetween, and the feed passageway extends axially through the first radial wall of the carrier.

3. The turbine shroud assembly of claim 2 , wherein the first radial wall is formed to include a feed cavity configured to receive cooling air from a cooling air source and the feed passageway are in fluid communication with the feed cavity.

4. The turbine shroud assembly of claim 2 , wherein the at least one pin includes a first end located adjacent to the first radial wall, a second end spaced apart axially from the first end of the pin and located adjacent to the second radial wall, and a body that extends between and interconnects the first end and the second end, the second end shaped to include a recess that extends axially into the second end of the pin so that an outlet of cooling passageway is spaced apart axially from the second radial wall.

5. The turbine shroud assembly of claim 1 , wherein the at least one pin includes a first end located adjacent an outlet of the feed passageway in the carrier, a second end spaced apart axially from the first end of the pin, and a body that extends between and interconnects the first end and the second end, the second end shaped to include a recess that extends axially into the second end of the pin.

6. The turbine shroud assembly of claim 5 , wherein the feed passageway has a first diameter and the cooling passageway has a second diameter that is greater than the first diameter of the feed passageway.

7. The turbine shroud assembly of claim 6 , wherein the second diameter of the cooling passageway varies along an axial length of the at least one pin.

8. The turbine shroud assembly of claim 7 , wherein the second diameter of the cooling passageway has a maximum value at the first end of the at least one pin and the second end of the at least one pin and a minimum value proximate an axial center of the at least one pin.

9. The turbine shroud assembly of claim 5 , wherein the first end of the pin forms a pin head located adjacent an outlet of the feed passageway and a body that extends axially from the pin and has a first diameter that is less than a second diameter of the pin head.

10. The turbine shroud of claim 1 , wherein the feed passageway has a first diameter and the cooling passageway has a second diameter that is greater than the first diameter of the feed passageway.

11. The turbine shroud of claim 10 , wherein the second diameter of the cooling passageway varies along an axial length of the at least one pin.

12. A turbine shroud assembly adapted for use in a gas turbine engine, the turbine shroud assembly comprising

a carrier that extends at least partway circumferentially around an axis, the carrier formed to include a feed passageway configured to conduct cooling air through a portion of the carrier,

a blade track segment including a runner shaped to extend partway around the axis and an attachment portion that extends radially outward from the runner, and

an intermediate carrier including an intermediate carrier body, a pin that extends axially into the attachment portion and the intermediate carrier body to couple the intermediate carrier body to the blade track segment, and a first retainer that extends through the carrier to couple the intermediate carrier and the blade track segment to the carrier,

wherein the pin is formed to include a cooling passageway that extends axially through the pin and aligns with the feed passageway of the carrier such that cooling air is configured to be conducted from the feed passageway through the pin to cool the pin.

13. The turbine shroud assembly of claim 12 , wherein the carrier includes an outer wall that extends circumferentially at least partway about the axis, a first radial wall that extends radially inward from the outer wall, and a second radial wall that extends radially inward from the outer wall, the second radial wall is spaced apart from the first radial wall to define an attachment-receiving space therebetween, and the feed passageway extends axially through the first radial wall of the carrier.

14. The turbine shroud assembly of claim 13 , wherein the pin includes a first end located adjacent to the first radial wall, a second end spaced apart axially from the first end of the pin and located adjacent to the second radial wall, and a body that extends between and interconnects the first end and the second end, the second end shaped to include a recess that extends axially into the second end of the pin so that an outlet of cooling passageway is spaced apart axially from the second radial wall.

15. The turbine shroud assembly of claim 12 , wherein the pin includes a first end located adjacent an outlet of the feed passageway in the carrier, a second end spaced apart axially from the first end of the pin, and a body that extends between and interconnects the first end and the second end, the second end shaped to include a recess that extends axially into the second end of the pin.

16. The turbine shroud assembly of claim 12 , wherein the feed passageway has a first diameter and the cooling passageway has a second diameter that is greater than the first diameter of the feed passageway.

17. The turbine shroud assembly of claim 16 , wherein the second diameter of the cooling passageway varies along an axial length of the pin.

18. The turbine shroud assembly of claim 12 , wherein the pin includes a pin head located adjacent an outlet of the feed passageway and a body that extends axially from the pin and has a first diameter that is less than a second diameter of the pin head.

19. A method comprising

providing a carrier, a blade track segment, and an intermediate carrier configured to couple the blade track segment to the carrier, the blade track segment including a runner shaped to extend partway around an axis, a first mount post that extends radially outward from the runner, and a second mount post spaced apart axially from the first mount post that extends radially outward from the runner, and the intermediate carrier including an intermediate carrier body, a pin, and a retainer, wherein the pin is formed to include a cooling passageway that extends axially through the pin,

arranging the intermediate carrier axially between the first mount post and the second mount post so that a pin hole formed in the intermediate carrier aligns circumferentially with a pin hole in the first mount post and a pin hole in the second mount post,

inserting the pin through the pin hole formed in the first mount post, the pin hole formed in the intermediate carrier, and the pin hole formed in the second mount post to couple the blade track segment to the intermediate carrier body,

arranging the intermediate carrier in an attachment space formed in the carrier so that a feed passageway formed in the carrier aligns with the cooling passageway formed in the pin,

coupling the retainer of the intermediate carrier with the carrier, and

directing a flow of cooling air from the feed passageway in the carrier, through the cooling passageway in the pin, and into the attachment space formed in the carrier to cool the pin.

20. The method of claim 19 , wherein the feed passageway has a first diameter and the cooling passageway has a second diameter that is greater than the first diameter of the feed passageway.