Turbine engine assembly with ceramic matrix composite components and end face seals

1. A gas turbine engine assembly comprising

a first component comprising ceramic matrix composite materials, the first component having a first radial outer surface that extends circumferentially partway around an axis and a first circumferential end face that extends radially inward from the first radial outer surface toward the axis,

a second component comprising ceramic matrix composite, the second component having a second radial outer surface that extends circumferentially partway around the axis and a second circumferential end face that extends radially inward from the second radial outer surface toward the axis, and the second circumferential end face facing being spaced apart circumferentially from the first circumferential end face of the first component to define a gap therebetween, and

a seal configured to block gases from flowing axially and radially between the first component and the second component, the seal includes an outer segment and a radial segment, the outer segment extends circumferentially along the first radial outer surface across the gap and along the second radial outer surface to allow for changes in a size of the gap due to thermal growth of the gas turbine engine assembly and the radial segment extends radially inward from the outer segment into the gap,

wherein the first component includes a radial innermost surface that is spaced apart radially from the first radial outer surface toward the axis, the seal includes an outer end and an inner end that is spaced apart radially from the outer end, and the inner end is radially flush with the radial innermost surface of the first component.

2. The gas turbine engine assembly of claim 1 , wherein the seal is T-shaped when viewed axially relative to the axis.

3. The gas turbine engine assembly of claim 2 , wherein the first circumferential end face is planar and extends between and contacts directly the first radial outer surface and the radial innermost surface of the first component.

4. The gas turbine engine assembly of claim 2 , wherein the first radial outer surface is formed to define a plurality of first channels that extend radially into the first component, the second radial outer surface is formed to define a plurality of second channels that extend radially into the second component, and the outer segment of the seal covers the plurality of first channels and the plurality of second channels.

5. The gas turbine engine assembly of claim 1 , where the seal is H-shaped when viewed axially relative to the axis.

6. The gas turbine engine assembly of claim 5 , wherein the seal includes an outer end and an inner end that is spaced apart radially from the outer end, and the inner end is radially flush with the radial innermost surface of the first component.

7. The gas turbine engine assembly of claim 6 , wherein the first radial outer surface is the outermost surface of the first component in a radial direction relative to the axis.

8. The gas turbine engine assembly of claim 7 , wherein the first radial outer surface is formed to define a plurality of first channels that extend radially into the first component, the second radial outer surface is formed to define a plurality of second channels that extend radially into the first component, and the outer segment of the seal covers the plurality of first channels and the plurality of second channels.

9. The gas turbine engine assembly of claim 5 , wherein the seal further includes an inner segment spaced apart radially from the outer segment and the radial segment extends between and connects directly the inner segment and the outer segment.

10. The gas turbine engine assembly of claim 1 , wherein the first radial outer surface is formed to define a plurality of first channels that extend radially into the first component toward the axis, the second radial outer surface is formed to define a plurality of second channels that extend radially into the first component toward the axis, and the outer segment of the seal covers the plurality of first channels and the plurality of second channels.

11. The gas turbine engine assembly of claim 1 , wherein the first radial outer surface is the outermost surface of the first component in a radial direction relative to the axis.

12. The gas turbine engine assembly of claim 1 , wherein the first component includes a fore ridge and an aft ridge spaced apart axially from the fore ridge, the fore ridge and the aft ridge extend radially outward away from the first radial outer surface, the fore ridge extends circumferentially between a first end and a second end of the first component, and the aft ridge extends circumferentially between the first end and the second end of the first component.

13. A gas turbine engine assembly comprising

a first component comprising ceramic matrix composite materials, the first component extends circumferentially between a first end and second end thereof relative to an axis,

a second component comprising ceramic matrix composite materials, the second component extends circumferentially between a first end and second end thereof relative to the axis, and the first end of the second component is spaced apart circumferentially from the second end of the first component to define a gap therebetween, and

a seal configured to block gases from flowing between the first component and the second component, the seal includes an outer segment, a first leg segment, and a second leg segment, the outer segment extends circumferentially over the first radial outer surface, across the gap, and over the second radial outer surface, the first leg segment extends radially inward from the outer segment toward the axis and engages the first component, the second leg segment is spaced apart circumferentially from the first leg segment, and the second leg segment extends radially inward from the outer segment toward the axis and engages the second component,

wherein the first leg segment is formed to include a first channel that extends radially outward into the first leg segment, the second leg segment is formed to include a second channel that extends radially outward into the second leg segment, the first component covers the first channel, and the second component covers the second channel.

14. A gas turbine engine assembly comprising

a first component comprising ceramic matrix composite materials, the first component extends circumferentially between a first end and second end thereof relative to an axis,

a second component comprising ceramic matrix composite materials, the second component extends circumferentially between a first end and second end thereof relative to the axis, and the first end of the second component is spaced apart circumferentially from the second end of the first component to define a gap therebetween, and

a seal configured to block gases from flowing between the first component and the second component, the seal includes an outer segment, a first leg segment, and a second leg segment, the outer segment extends circumferentially over the first radial outer surface, across the gap, and over the second radial outer surface, the first leg segment extends radially inward from the outer segment toward the axis and engages the first component, the second leg segment is spaced apart circumferentially from the first leg segment, and the second leg segment extends radially inward from the outer segment toward the axis and engages the second component,

wherein the first leg segment includes a mating surface that engages the first component, the second leg segment includes a mating surface that engages the second component, and the mating surface of the first leg segment and the mating surface of the second leg segment are curvilinear to allow the seal to remain engaged with the first and second components in response to relative radially radial movement between the first component and the second component.

15. The gas turbine engine assembly of claim 13 , wherein the first component includes a radial outer surface that engages the first leg segment and an axially extending ridge located at the second end of the first component and the axially extending ridge further extends radially outward away from the first radial outer surface toward the outer segment of the seal into a space defined circumferentially between the first leg segment and the second leg segment.

16. The gas turbine engine assembly of claim 15 , wherein the first leg segment is spaced apart circumferentially from the axially extending ridge to allow the first component to move circumferentially relative to the second component.

17. The gas turbine engine assembly of claim 15 , wherein the first component includes a fore ridge and an aft ridge spaced apart axially from the fore ridge, the fore ridge and the aft ridge extend radially outward away from the first radial outer surface, the fore ridge extends circumferentially between the first end and the second end of the first component, and the aft ridge extends circumferentially between the first end and the second end of the first component.