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An airfoil assembly includes an airfoil body extending between a leading edge, a trailing edge, a suction side, and a pressure side. A first sheath having an outer side and an inner side forms a cavity for receiving at least a portion of the airfoil body and is bonded on the inner side to the leadin

An airfoil assembly includes an airfoil body extending between a leading edge, a trailing edge, a suction side, and a pressure side. A first sheath having an outer side and an inner side forms a cavity for receiving at least a portion of the airfoil body and is bonded on the inner side to the leading edge of the airfoil body. The first sheath is formed of a titanium-based metallic material. A second sheath is bonded to the outer side of the first sheath.

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1. An airfoil assembly comprising: an airfoil body extending between a leading edge, a trailing edge, a suction side, and a pressure side;a first sheath including a first plate on the suction side of the airfoil body and a second plate on the pressure side of the airfoil body that meet at a seam at

1. An airfoil assembly comprising: an airfoil body extending between a leading edge, a trailing edge, a suction side, and a pressure side;a first sheath including a first plate on the suction side of the airfoil body and a second plate on the pressure side of the airfoil body that meet at a seam at a nose near the leading edge, the first sheath having an outer side and an inner side that forms a cavity for receiving at least a portion of the airfoil body, the inner side being bonded to the leading edge of the airfoil body, and the first sheath being formed from a titanium-based metallic material; anda second sheath bonded to the outer side of the first sheath. 2. The airfoil assembly as recited in claim 1, wherein a wall thickness of the first sheath tapers from a nose at the leading edge of the airfoil body to a rearward end of the first sheath. 3. The airfoil assembly as recited in claim 1, wherein the second sheath is formed of a nickel-based metallic material. 4. The airfoil assembly as recited in claim 1, further comprising an adhesive between the first sheath and the airfoil body. 5. The airfoil assembly as recited in claim 1, wherein the airfoil body is a composite material comprising a polymer matrix and reinforcement fibers distributed within the polymer matrix. 6. The airfoil assembly as recited in claim 1, wherein the airfoil body includes surface portions that are covered by the first sheath and other surface portions that are not covered by the first sheath, with a ratio of the covered portion to the uncovered portion that is about 0.1-1. 7. The airfoil assembly as recited in claim 1, wherein the inner side of the first sheath is in direct contact with the airfoil body, and the second sheath is adhesively bonded directly to the outer side of the first sheath. 8. The airfoil assembly as recited in claim 1, wherein the second sheath is seam-free. 9. The airfoil assembly as recited in claim 1, wherein the second sheath has a free outer surface. 10. The airfoil assembly as recited in claim 1, wherein the second sheath has a free outer surface at a nose. 11. The airfoil assembly as recited in claim 1, wherein the second sheath is formed of a nickel-based metallic material, the first sheath providing ductility that absorbs energy from an impact and the second sheath providing a lower ductility and a higher hardness for erosion. 12. An airfoil assembly comprising: an airfoil body extending between a leading edge, a trailing edge, a suction side, and a pressure side;a first sheath having an outer side and an inner side that forms a cavity for receiving at least a portion of the airfoil body, the inner side being bonded to the leading edge of the airfoil body, the first sheath being formed from a titanium-based metallic material, the first sheath including a first plate on the suction side of the airfoil body and a second plate on the pressure side of the airfoil body that meet at a nose near the leading edge, wherein the first plate and the second plate include respective notches that abut against the leading edge of the airfoil body, the first plate and the second plate each having a uniform wall thickness from the respective notches to a tip of the nose, and wherein the nose of the first sheath extends forward relative to the leading edge of the airfoil body and includes a seam where the first plate and the second plate meet; anda second sheath bonded to the outer side of the first sheath. 13. A sheath for an airfoil assembly, comprising: a first sheath body including a first plate and a second plate that meet at a seam at a nose, the first sheath body having an outer side and an inner side that forms a cavity for receiving at least a portion of an airfoil body, the first sheath being formed of a titanium-based metallic material; anda second, metal sheath body bonded to the outer side of the first sheath body. 14. The sheath as recited in claim 13, wherein a wall thickness of the first sheath tapers from a nose to a rearward end of the first sheath. 15. The sheath as recited in claim 13, wherein the second sheath is formed of a nickel-based metallic material, the first sheath providing ductility that absorbs energy from an impact and the second sheath providing a lower ductility and a higher hardness for erosion. 16. A sheath for an airfoil assembly, comprising: a first sheath body having an outer side and an inner side that forms a cavity for receiving at least a portion of an airfoil body, the first sheath being formed of a titanium-based metallic material, the first sheath including a first plate and a second plate that meet at a nose, the nose extending forward relative to the cavity and including a seam where the first plate and the second plate meet, and wherein the first plate and the second plate include respective notches within the cavity, the first plate and the second plate each having a uniform wall thickness from the respective notches to a tip of the nose; anda second sheath body bonded to the outer side of the first sheath body. 17. A method for protecting an airfoil assembly, comprising: providing an airfoil body that extends between a leading edge, a trailing edge, a suction side, and a pressure side with a first sheath and a second sheath bonded to an outer side of the first sheath, the first sheath including a first plate on the suction side of the airfoil body and a second plate on the pressure side of the airfoil body that meet at a seam at a nose near the leading edge, the first sheath having an inner side that forms a cavity for receiving at least a portion of the airfoil body, the inner side being bonded to the leading edge of the airfoil, and the first sheath being formed of a titanium-based metallic material. 18. The method as recited in claim 17, further comprising selecting the second sheath to be a nickel-based metallic material.