Airfoil with sandwich composite
An airfoil for a gas turbine engine includes an airfoil section and a platform that has a non-gaspath side and a gaspath side from which the airfoil section extends. The platform is comprised of a sandwich composite that has first and second ceramic matrix composite (CMC) skins that each include at least one 2-D ceramic fiber ply. The first and second CMC skins are disposed, respectively, on the gaspath side and the non-gaspath side, and there is a cellular core disposed radially between the first and second CMC skins.
1. An airfoil for a gas turbine engine comprising:
an airfoil section; and
a platform having a non-gaspath side and a gaspath side from which the airfoil section extends, the platform being comprised of a sandwich composite including first and second ceramic matrix composite (CMC) skins each including at least one 2-D ceramic fiber ply, the first and second CMC skins being disposed, respectively, on the gaspath side and the non-gaspath side, and a cellular core disposed radially between the first and second CMC skins.
2. The airfoil as recited in claim 1 , wherein the cellular core is selected from the group consisting of a honeycomb, a foam, a ceramic felt, a 3-D fabric, a monolithic ceramic grid, and combinations thereof.
3. The airfoil as recited in claim 1 , wherein the cellular core is selected from the group consisting of a honeycomb, a foam, a monolithic ceramic grid, and combinations thereof.
4. The airfoil as recited in claim 1 , wherein the first and second CMC skins turn from the platform and converge with each other into the airfoil section.
5. The airfoil as recited in claim 1 , wherein the cellular core extends into the airfoil section.
6. The airfoil as recited in claim 1 , wherein the cellular core includes cells that are void.
7. The airfoil as recited in claim 1 , wherein the cellular core includes cells that include a filler material.
8. The airfoil as recited in claim 7 , wherein the filler material is selected from the group consisting of a monolithic ceramic and a fibrous ceramic.
9. The airfoil as recited in claim 1 , wherein the cellular core has a contoured surface profile, and at least one of the first or second CMC skins conforms to the contoured surface profile.
10. The airfoil as recited in claim 9 , wherein the contoured surface profile is on the gaspath side of the cellular core.
11. The airfoil as recited in claim 1 , wherein the cellular core has a first contoured surface profile on the gaspath side of the cellular core, a second contoured profile on the non-gaspath side of the cellular core, the first CMC skin conforms to the first contoured surface profile, and the second CMC skin conforms to the second contoured surface profile.
12. The airfoil as recited in claim 11 , wherein the second contoured surface profile tracks the first contoured surface profile.
13. The airfoil as recited in claim 11 , wherein the second contoured surface profile mirrors the first contoured surface profile.
14. A gas turbine engine comprising:
a compressor section;
a combustor in fluid communication with the compressor section; and
a turbine section in fluid communication with the combustor, the turbine section having an airfoil including
an airfoil section, and
a platform having a non-gaspath side and a gaspath side from which the airfoil section extends, the platform being comprised of a sandwich composite including first and second ceramic matrix composite (CMC) skins each including at least one 2-D ceramic fiber ply, the first and second CMC skins being disposed, respectively, on the gaspath side and the non-gaspath side, and a cellular core disposed radially between the first and second CMC skins.