Joint for band features on turbine nozzle and fabrication
A ceramic matrix composite (CMC) component including a subcomponent, such as a band flowpath, a load bearing wall and a wall support, each comprised of a ceramic matrix composite (CMC) including reinforcing fibers embedded in a matrix. The CMC component further including at least one mechanical joint joining the subcomponent, the load bearing wall and the wall support to form the CMC component. The reinforcing fibers of the load bearing wall are oriented substantially normal to the reinforcing fibers of the subcomponent and the wall support. Methods are also provided for joining the subcomponent, the load bearing wall and the wall support to form a mechanical joint.
1. A ceramic matrix composite (CMC) component for forming a portion of a nozzle for a gas turbine engine comprising:
a subcomponent comprised of a ceramic matrix composite (CMC) including reinforcing fibers embedded in a matrix;
a load bearing wall comprised of a ceramic matrix composite (CMC) including reinforcing fibers embedded in a matrix;
a wall support comprised of a ceramic matrix composite (CMC) including reinforcing fibers embedded in a matrix; and
at least one joint joining the subcomponent, the load bearing wall and the wall support,
wherein the reinforcing fibers of the load bearing wall are oriented normal to the reinforcing fibers of the subcomponent and the wall support.
2. The component of claim 1 , wherein the wall support is integrally formed with the subcomponent.
3. The component of claim 1 , wherein the wall support is separate and distinct from the subcomponent.
4. The component of claim 1 , wherein the at least one joint is an interlocking joint comprising at least one tab defined in the wall support and cooperatively engaged with a respective at least one recess formed in the load bearing wall.
5. The component of claim 1 , wherein the load bearing wall is configured as a dovetail shaped load bearing wall.
6. The component of claim 1 , wherein the load bearing wall is configured as a wedge-shaped load bearing wall.
7. The component of claim 6 , wherein the reinforcing fibers of the wedge-shaped load bearing wall are oriented normal to the reinforcing fibers in the subcomponent and the wall support.
8. The component of claim 1 , further comprising a secondary wall support.
9. The component of claim 8 , wherein the at least one joint is an interlocking joint comprising at least one tab defined in the secondary wall support and cooperatively engaged with a respective at least one recess formed in the load bearing wall.
10. The component of claim 1 , wherein the at least one joint is an interlocking joint comprising at least one ceramic matrix composite (CMC) pin, each disposed in a slot in the load bearing wall and cooperatively engaged therewith.
11. The component of claim 1 , wherein the load bearing wall is disposed in a recess formed in an uppermost surface of the subcomponent.
12. The component of claim 11 , wherein the wall support is disposed in the recess formed in the uppermost surface of the subcomponent.
13. The component of claim 11 , wherein the wall support is disposed on the uppermost surface of the subcomponent.
14. The component of claim 1 , wherein the load bearing wall is disposed on an uppermost surface of the subcomponent.
15. The component of claim 14 , wherein the wall support is disposed on the uppermost surface of the subcomponent.
16. A portion of a nozzle for a gas turbine comprising:
a band comprising:
a band flowpath comprised of a ceramic matrix composite (CMC) including reinforcing fibers embedded in a matrix, the band flowpath having an opening defined therein;
a load bearing wall comprised of a ceramic matrix composite (CMC) including reinforcing fibers embedded in a matrix;
a wall support comprised of a ceramic matrix composite (CMC) including reinforcing fibers embedded in a matrix; and
at least one joint joining the band flowpath, the load bearing wall and the wall support to form a portion of a CMC component,
wherein the reinforcing fibers of the load bearing wall are oriented normal to the reinforcing fibers of the band flowpath and the wall support.
17. The nozzle of claim 16 , wherein the at least one joint is an interlocking joint comprising one or more tabs defined in the wall support and cooperatively engaged with a response one or more recesses formed in the load bearing wall.
18. The nozzle of claim 16 , further comprising a secondary wall support.
19. The nozzle of claim 18 , wherein the at least one joint is an interlocking joint comprising one or more tabs defined in the secondary wall support and cooperatively engaged with a respective one or more recesses formed in the load bearing wall.
20. The nozzle of claim 16 , wherein the at least one joint is an interlocking joint comprising a dove-tailed shaped load bearing wall cooperatively engaged with a respective recess formed in the band flowpath.
21. The nozzle of claim 16 , wherein the at least one interlocking joint comprises a wedge shaped load bearing wall.
22. The nozzle of claim 16 , wherein the at least one joint is an interlocking joint comprising at least one ceramic matrix composite (CMC) pin, each disposed in a slot in the load bearing wall and cooperatively engaged therewith.
23. A method of forming a ceramic matrix composite (CMC) component for forming a portion of a nozzle for a gas turbine engine comprising:
providing a subcomponent comprised of a ceramic matrix composite (CMC) including reinforcing fibers embedded in a matrix;
providing a load bearing wall comprised of a ceramic matrix composite (CMC) including reinforcing fibers embedded in a matrix;
providing a wall support comprised of a ceramic matrix composite (CMC) including reinforcing fibers embedded in a matrix; and
mechanically joining the subcomponent, the load bearing wall and the wall support to form a portion of a CMC component and to form at least one mechanical joint,
wherein the reinforcing fibers of the load bearing wall are oriented normal to the reinforcing fibers of the subcomponent and the wall support.