Airfoil with sandwich composite
AssigneeRtx Corporation
InventorsRussell Kim, Raymond Surace, James T. Roach, Jonas Banhos
Life of this patent
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Abstract
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.
Claims14
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.
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.
Dependencies are inferred from the claim text.