Ceramic matrix composite components reinforced for managing multi-axial stresses and methods for fabricating the same
Ceramic matrix composite components and methods for fabricating ceramic matrix composite components are provided. In one example, a ceramic matrix composite component includes a ceramic matrix composite body. The ceramic matrix composite body includes a layer-to-layer weave of ceramic fibers and a layer of 1-directional and/or 2-directional (1D/2D) fabric of ceramic fibers disposed adjacent to the layer-to-layer weave. When stressed, the ceramic matrix composite body forms a relatively high through-thickness stress region and a relatively high in-plane bending stress region. The layer-to-layer weave is disposed through the relatively high through-thickness stress region and the layer of 1D/2D fabric is disposed through the relatively high in-plane bending stress region.
1. A ceramic matrix composite component, the ceramic matrix composite component comprising:
a ceramic matrix composite body comprising a layer-to-layer weave of ceramic fibers and at least one layer of 1-directional and/or 2-directional (1D/2D) fabric of ceramic fibers disposed adjacent to the layer-to-layer weave, the ceramic matrix composite body including a relatively high through-thickness stress region and a relatively high in-plane bending stress region, the layer-to-layer weave is disposed through the relatively high through-thickness stress region and the at least one layer of 1D/2D fabric is disposed through the relatively high in-plane bending stress region,
wherein the ceramic matrix composite body includes an inside-facing outer surface section and an interior mid-section surrounding the inside-facing outer surface section, and wherein the at least one layer of 1D/2D fabric is disposed in the inside-facing outer surface section and the layer-to-layer weave is disposed in the interior mid-section.
2. The ceramic matrix composite component of claim 1 , wherein the layer-to-layer weave comprises a 2.5-dimensional weave of ceramic fibers.
3. The ceramic matrix composite component of claim 1 , wherein the layer-to-layer weave comprises a 3-dimensional weave of ceramic fibers.
4. The ceramic matrix composite component of claim 1 , wherein the ceramic matrix composite body is a component of a gas turbine engine.
5. The ceramic matrix composite component of claim 4 , wherein the ceramic matrix composite body is a seal segment of the gas turbine engine, wherein the inside-facing outer surface section is substantially concave.
6. The ceramic matrix composite component of claim 4 , wherein the ceramic matrix composite body is a vane or blade of the gas turbine engine.
7. The ceramic matrix composite component of claim 6 , wherein the vane or blade of the gas turbine engine is an internally cooled vane or blade, wherein the inside-facing outer surface section surrounds a cooling channel.
8. The ceramic matrix composite component of claim 1 , wherein the relatively high in-plane bending stress region includes a relatively high in-plane tensile stress region and a relatively high in-plane compression stress region, wherein the relatively high through-thickness stress region is disposed between the relatively high in-plane tensile stress region and the relatively high in-plane compression stress region, and wherein the at least one layer of 1D/2D fabric is disposed through the relatively high in-plane tensile stress region.
9. The ceramic matrix composite component of claim 8 , wherein the at least one layer of 1D/2D fabric is disposed through the relatively high in-plane compression stress region.
10. The ceramic matrix composite component of claim 8 , wherein the layer-to-layer weave is disposed through the relatively high in-plane compression stress region.
11. A method for fabricating a ceramic matrix composite component, the method comprising:
forming a porous ceramic preform into a ceramic matrix composite body, wherein the porous ceramic preform comprises a layer-to-layer weave of ceramic fibers and at least one layer of 1-directional and/or 2-directional (1D/2D) fabric of ceramic fibers by:
arranging, the at least one layer of 1D/2D fabric on an inside facing surface of the ceramic matrix composite body in a relatively high in-plane bending stress region of the ceramic matrix composite body; and
arranging the layer-to-layer weave in an interior mid-section surrounding the inside-facing outer surface section in a relatively high through-thickness stress region of the ceramic matrix composite body.
12. The method of claim 11 , wherein forming the ceramic matrix composite body comprises:
infiltrating a molten metal or alloy into the porous ceramic preform; and
solidifying the molten metal or alloy to form the ceramic matrix composite body.
13. The method of claim 11 , further comprising providing the porous ceramic preform comprising forming a layup that comprises the layer-to-layer weave and the at least one layer of 1D/2D fabric disposed adjacent to the layer-to-layer weave.
14. The method of claim 13 , wherein forming the layup comprises arranging the layer-to-layer weave comprising a 2.5-dimensional weave of ceramic fibers in the layup.
15. The method of claim 13 , wherein forming the layup comprises arranging the layer-to-layer weave comprising a 3-dimensional weave of ceramic fibers in the layup.
16. A ceramic matrix composite component, the ceramic matrix composite component comprising:
a ceramic matrix composite body comprising a layer-to-layer weave of ceramic fibers and at least one layer of 1-directional and/or 2-directional (1D/2D) fabric of ceramic fibers disposed adjacent to the layer-to-layer weave,
the ceramic matrix composite body including a relatively high in-plane bending stress region, the relatively high in-plane bending stress region including a relatively high in-plane tensile stress region, a relatively high in-plane compression stress region,
wherein the at least one layer of 1-directional and/or 2-directional (1D/2D) fabric of ceramic fibers is disposed in the relatively high in-plane tensile stress region and the layer-to-layer weave is disposed in the relatively high in-plane compression stress region.
17. The ceramic matrix composite component of claim 16 , wherein a relatively high through-thickness stress region disposed between the relatively high in-plane tensile stress region and the relatively high in-plane compression stress region.
18. The ceramic matrix composite component of claim 17 , wherein the ceramic matrix composite body has an outer surface section and an interior mid-section that is disposed adjacent to the outer surface section, wherein the at least one layer of 1D/2D fabric is disposed in the outer surface section of the ceramic matrix composite body, and wherein the layer-to-layer weave is disposed in the interior mid-section of the ceramic matrix composite body.
19. The ceramic matrix composite component of claim 16 , wherein ceramic matrix composite body is a non-internally cooled vane or blade of a gas turbine engine having an outer surface section that surrounds a substantially solid interior mid-section, and wherein the at least one layer of 1D/2D fabric is disposed in the outer surface section and the layer-to-layer weave is disposed in the substantially solid interior mid-section of the non-internally cooled vane or blade.
20. The ceramic matrix composite component of claim 16 , wherein the ceramic matrix composite body is an annular ceramic matrix composite combustor of a gas turbine engine, wherein the annular ceramic matrix composite combustor has an interior mid-section surrounding a cooling channel and an outside-facing outer surface section that surrounds the interior mid-section, and wherein the at least one layer of 1D/2D fabric is disposed in the outside-facing outer surface section and the layer-to-layer weave is disposed in the interior mid-section of the annular ceramic matrix composite combustor.