CPC F01D 5/282 (2013.01) [F01D 5/147 (2013.01); F01D 5/284 (2013.01); F05D 2240/80 (2013.01); F05D 2250/283 (2013.01); F05D 2300/6033 (2013.01); F05D 2300/612 (2013.01)] | 14 Claims |
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.
|