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A blade or a vane preferably used in a gas turbine engine, the blade or vane being formed of a metallic core or insert with a ceramic airfoil surface bonded to the metallic insert. The insert includes a series of concave and convex portions arranged along the outer surface, in which a plurality of h

A blade or a vane preferably used in a gas turbine engine, the blade or vane being formed of a metallic core or insert with a ceramic airfoil surface bonded to the metallic insert. The insert includes a series of concave and convex portions arranged along the outer surface, in which a plurality of hoop fibers are secured within a resin matrix to firmly secure the metallic insert to the ceramic airfoil body. Axial loads between the insert and the ceramic body are transferred to the hoop fibers. The hoop fibers are strong enough to resist extending in length that would permit the hoop fibers from sliding over the widest portion of the insert.

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I claim the following: 1. An airfoil, comprising: a metallic insert having an outer surface forming a plurality of concave portions and a plurality of convex portions around its outer surface; a ceramic airfoil having a hollow section, the metallic insert fitting within the hollow ceramic airfoil;

I claim the following: 1. An airfoil, comprising: a metallic insert having an outer surface forming a plurality of concave portions and a plurality of convex portions around its outer surface; a ceramic airfoil having a hollow section, the metallic insert fitting within the hollow ceramic airfoil; a resin matrix material substantially filling a space formed between an inner surface of the ceramic airfoil and the outer surface of the metallic insert; and, a plurality of hoop fibers embedded into the resin matrix and located substantially within the concave portions of the metallic insert. 2. The airfoil of claim 1, and further comprising: the ceramic airfoil includes inner and outer shrouds extending from the airfoil portion to form a vane. 3. The airfoil of claim 1, and further comprising: the metallic insert includes a cooling fluid passage extending through the insert. 4. The airfoil of claim 1, and further comprising: the insert includes a root member to form a blade, the root member including means to secure the root to a slot in a rotor disc. 5. A process for forming an airfoil comprising the steps of: forming a metallic insert having a series of concave and convex portions on the outer surface of the insert; placing a plurality of fiber hoop members within the concave portions of the insert; placing the insert with the hoop fibers within a hollow portion of a ceramic airfoil; and, filling the space formed between the inner surface of the hollow portion of the ceramic airfoil and the outer surface of the insert to secure the hoop fibers. 6. The process for forming the airfoil of claim 5, and further comprising the step of: forming a cooling passage extending through the insert. 7. The process for forming the airfoil of claim 5, and further comprising the step of: forming an inner shroud and an outer shroud on the ceramic airfoil to form a vane. 8. The process for forming the airfoil of claim 5, and further comprising the step of: forming a root portion of the insert to form a blade, the root portion having means to secure the blade to a slot in a rotor disc. 9. A ceramic and metallic airfoil for use in a gas turbine engine, the ceramic and metallic airfoil comprising: an airfoil having a leading edge and a trailing edge, and a pressure side and a suction side extending between the leading edge and the trailing edge; the airfoil being formed from a high temperature resistant ceramic material; a metallic insert, the insert having an outer surface forming a concave surface; a plurality of fibers wrapping around the metallic insert within the concave surface; and, a resin matrix filling a space formed between an inner wall of the ceramic airfoil and the outer surface of the metallic insert to provide for a bond between the ceramic airfoil and the insert and to hold the fibers in place within the concave surface. 10. The ceramic and metallic airfoil of claim 9, and further comprising: the metallic insert includes a plurality of concave surfaces each with a plurality of fibers wrapping around the insert. 11. The ceramic and metallic airfoil of claim 9, and further comprising: the concave surface is formed around the entire insert. 12. The ceramic and metallic airfoil of claim 9, and further comprising: the fibers are high temperature resistant fibers capable of use within a gas turbine engine environment. 13. The ceramic and metallic airfoil of claim 9, and further comprising: the metallic insert includes a cooling fluid passage extending though the insert. 14. The ceramic and metallic airfoil of claim 9, and further comprising: the fibers are one or more long fibers that wrap around the insert a number of times to form a plurality of hoop fibers. 15. The ceramic and metallic airfoil of claim 9, and further comprising: the airfoil includes a plurality of holes extending in the airfoil spanwise direction; and, a metallic insert extending through each of the plurality of holes, each insert having a concave outer surface with a plurality of hoop fibers held within the concave surface and wrapping around the insert. 16. The ceramic and metallic airfoil of claim 9, and further comprising: the airfoil is a turbine rotor blade; and, the metallic insert includes a root portion with a fir-tree configuration for inserting the blade into a slot within a rotor disk of the turbine. 17. The ceramic and metallic airfoil of claim 9, and further comprising: the airfoil is a turbine stator vane; and, the metallic insert is secured between an inner shroud and an outer shroud to form a hot gas path through the stator vane.