Ceramic matrix composite turbine engine component
Aspects of the invention are directed to a gas turbine component such as a ring seal segment or combustor heat shield having a base and a plurality of walls defining a volume. The base and the walls are independently formed and are formed from ceramic matrix composite plates. The base and walls can have interconnection structures that allow for assembly. The base and walls can be coated or otherwise wrapped for connection. Locking mechanisms, such as self locking lugs, can be used for assembly.
1 . A turbine engine component comprising:
a body having a base and a plurality of walls, each of the base and the plurality of walls being ceramic matrix composite plates that are independently formed, the base and the plurality of walls having interconnection structures, the body being assembled by the interconnection structures to define a volume therein.
2 . The component of claim 1 , wherein the body defines an open-ended structure.
3 . The component of claim 1 , wherein the interconnection structures are projections that mate with corresponding recesses.
4 . The component of claim 3 , wherein the recesses extend completely through each of the plurality of walls and wherein the projections extend through the recesses beyond the plurality of walls.
5 . The component of claim 4 , further comprising locking mechanisms that lock the projections in the recesses.
6 . The component of claim 5 , wherein the locking mechanisms are pins that are positioned through holes in the projections.
7 . The component of claim 4 , wherein the projections have self-locking mechanisms formed thereon.
8 . The component of claim 1 , wherein a wrap is applied on at least a portion of the body to fix the plurality of walls.
9 . The component of claim 3 , wherein a wrap is applied on at least a portion of the body to fix the base to the plurality of walls, wherein the recesses are completely through each of the plurality of walls, wherein at least two of the projections extend through the recesses beyond the plurality of walls and wherein the wrap is disposed between the at least two projections.
10 . The component of claim 3 , wherein the recesses extend completely through each of the plurality of walls, wherein the projections extend through the recesses beyond the plurality of walls, wherein a coating is applied over at least a portion of a surface of the body and wherein the coating fills at least one gap in the body.
11 . A turbine engine component comprising:
a body formed by a process of independently manufacturing a plurality of plates, each of the plurality of plates being ceramic matrix composites, the plurality of plates having interconnection structures and being assembled by the interconnection structures to define a volume therein, wherein at least one of a coating or a wrap is applied on at least a portion of the body to fix the plurality of plates.
12 . The component of claim 11 , wherein the body defines an open-ended structure.
13 . The component of claim 11 , wherein the interconnection structures are projections that mate with corresponding recesses.
14 . The component of claim 13 , wherein the recesses extend completely through each of the plurality of plates.
15 . The component of claim 14 , further comprising locking mechanisms that lock the projections in the corresponding recesses.
16 . The component of claim 13 , wherein the projections have self-locking mechanisms formed thereon.
17 . The component of claim 11 , wherein the component is a ring seal segment or a combustor heat shield.
18 . A method of manufacturing a ceramic matrix composite gas turbine component comprising:
independently forming a plurality of plates from ceramic matrix composites;
assembling the plurality of plates to define a volume therein; and
applying a wrap to an outer surface of the plurality of plates to fix the plurality of plates to each other.
19 . The method of claim 18 , further comprising forming each of the plurality of plates with at least one interconnection structure that connects to at least one interconnection structure of another of the plurality of plates.
20 . The method of claim 19 , further comprising forming locking mechanisms made from ceramic matrix composites that lock each of the at least one interconnection structures.