Insert-mounted turbine assembly for a gas turbine engine

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

a seal segment comprising ceramic matrix composite materials, the seal segment including a shroud wall that extends circumferentially partway around an axis to define a gas path boundary of the turbine assembly and a mount post that extends radially outward away from the shroud wall,

a carrier comprising metallic materials and configured to support the seal segment in position radially relative to the axis, the carrier including an outer wall that extends circumferentially at least partway about the axis, a first attachment flange that extends radially inward from the outer wall, and a second attachment flange that extends radially inward from the outer wall and spaced apart axially from the first attachment flange to define a radially inwardly opening channel that receives the mount post of the seal segment, and

a mounting insert coupled with the carrier and engaged with the mount post of the seal segment to bias the seal segment into engagement with the carrier with a predetermined force, the mounting insert including an insert body fixed to the first attachment flange, a protrusion that extends axially between a first end coupled with the insert body and a second end engaged with the mount post of the seal segment to define a receiving space between the first end and the second end of the protrusion, and a bias member located in the receiving space and engaged with the insert body and the mount post to apply a force to the mount post and limit axial movement of the seal segment relative to the carrier,

wherein the receiving space has a predetermined axial length between the first end and the second end of the protrusion to control an amount of compression of the bias member between the insert body and the mount post so that the force applied by the bias member to the seal segment is within a predetermined force threshold range.

2. The turbine assembly of claim 1 , wherein the first attachment flange of the carrier is shaped to include a through hole and the insert body extends into the through hole to fix the insert body to the first attachment flange.

3. The turbine assembly of claim 2 , wherein the protrusion extends around an outer perimeter edge of the insert body to form a rim around the insert body.

4. The turbine assembly of claim 3 , wherein the mounting insert further includes a shaft that extends axially from the insert body through the first attachment flange and the mount post and into the second attachment flange to interlock the seal segment with the carrier.

5. The turbine assembly of claim 4 , wherein the protrusion includes a rigid member that extends from the insert body toward the mount post and a fugitive member located axially between the rigid member and the mount post of the seal segment.

6. The turbine assembly of claim 1 , wherein the protrusion is spaced apart from an outer perimeter edge of the insert body.

7. The turbine assembly of claim 6 , wherein the mounting insert further includes a rim that extends around the outer perimeter edge of the insert body, the bias member is arranged around the protrusion, and the rim has an axial rim length that is less than the predetermined axial length so that the rim is spaced apart axially from the mount post.

8. The turbine assembly of claim 7 , wherein the mounting insert further includes a shaft that extends axially from the protrusion through the first attachment flange and the mount post and into the second attachment flange to interlock the seal segment with the carrier.

9. The turbine assembly of claim 1 , wherein the second attachment flange includes a radially extending wall and a contact pad that extends axially from the radially extending wall toward the first attachment flange and engages the mount post of the seal segment.

10. The turbine assembly of claim 9 , wherein the mounting insert further includes a shaft that extends from the protrusion through the first attachment flange and the mount post and into the contact pad of the second attachment flange.

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

a first component,

a second component, and

a mounting insert that includes an insert body fixed to the second component, a protrusion that extends away from the insert body toward the first component to a terminal end of the protrusion that is engaged with the first component to define a receiving space having a predetermined length between the insert body and the terminal end of the protrusion, and a bias member located in the receiving space and engaged with the insert body and the first component,

wherein the second component includes an outer wall that extends circumferentially at least partway about an axis, a first attachment flange that extends radially away from the outer wall, and a second attachment flange that extends radially away from the outer wall and is spaced apart from the first attachment flange to define a channel that receives the first component.

12. The turbine assembly of claim 11 , wherein the mounting insert is interference fit with the second component.

13. The turbine assembly of claim 11 , wherein the protrusion is arranged around an outer perimeter edge of the insert body.

14. The turbine assembly of claim 13 , wherein the mounting insert further includes a shaft that extends from the insert body through the second component and the first component to interlock the first component with the second component.

15. The turbine assembly of claim 13 , wherein the protrusion includes a rigid member coupled with the insert body and a fugitive member coupled with the rigid member and engaged with the first component.

16. The turbine assembly of claim 11 , wherein the protrusion is spaced apart from an outer perimeter edge of the insert body.

17. The turbine assembly of claim 16 , wherein the mounting insert further includes a rim arranged around the outer perimeter edge of the insert body and the rim is spaced apart from the first component.

18. The turbine assembly of claim 11 , wherein the first component is a turbine vane, the second component is a support structure coupled with the turbine vane, and the mounting insert is coupled with the support structure and engaged with the turbine vane.

19. A method comprising

providing a first component, a second component, and a mounting insert, the mounting insert including an insert body that extends into the second component, a protrusion that extends from a first surface of the insert body toward the first component and terminates at a second surface to define a receiving space therebetween, and a bias member,

locating the bias member in the receiving space,

locating the first component in a channel formed in the second component,

inserting the mounting insert into the second component so that the protrusion and the bias member engage the first component, and

fixing the insert body to the second component.