Airfoil assembly with ceramic airfoil pieces and seal

1. An airfoil assembly comprising:

first and second ceramic airfoil pieces each having first and second platforms and a hollow airfoil section connecting the first and second platforms;

first and second spars extending through, respectively, the hollow airfoil sections; and

a seal having a seal body defining at least one orifice and a seal portion, the first spar extending through one of the at least one orifices and the seal portion bridging a mate face between the first platforms of the first and second ceramic airfoil pieces, wherein each of the hollow airfoil sections defines a longitudinal direction between inner and outer ends and the seal portion is longitudinally offset from the at least one orifice.

2. The airfoil assembly as recited in claim 1 , wherein the seal is metal.

3. The airfoil assembly as recited in claim 2 , wherein the seal is formed of sheet metal.

4. The airfoil assembly as recited in claim 1 , wherein the seal portion terminates short of a leading edge and a trailing edge of the first platform.

5. The airfoil assembly as recited in claim 1 , wherein the at least one orifice includes first and second orifices, and the seal portion is between the first and second orifices.

6. The airfoil assembly as recited in claim 5 , wherein the first spar extends through the first orifice and the second spar extends through the second orifice.

7. The airfoil assembly as recited in claim 1 , further comprising a second seal that includes another seal body, another orifice, and another seal portion, the second spar extends through the orifice of the second seal, and the second seal partially overlaps the seal through which the first spar extends.

8. The airfoil assembly as recited in claim 1 , wherein the seal body defines a first, outer ring; a second, inner ring; and at least one spoke connecting the first ring and the second ring, where the at least one orifice is in the second ring and the seal portion is on the first ring.

9. The airfoil assembly as recited in claim 8 , wherein the the first ring is longitudinally offset from the second ring.

10. The airfoil assembly as recited in claim 8 , wherein the first ring defines a channel.

11. The airfoil assembly as recited in claim 1 , wherein the seal is a first seal, and further comprising a second seal that is identical to the first seal, the at least one orifice of the first seal and the second seal includes first and second orifices, and the seal portion of the first seal and the second seal is between the first and second orifices.

12. The airfoil assembly as recited in claim 11 , wherein the first spar extends through the first orifice of the first seal, the second spar extends through the second orifice of the first seal and also through the first orifice of the second seal such that the first and second seals partially overlap, and the seal portion of the first seal bridges the mate face between the first platforms of the first and second ceramic airfoil pieces.

13. The airfoil assembly as recited in claim 1 , wherein the seal body defines a first, outer ring, a second, inner ring, an open annular space between the inner and outer rings, and at least one spoke extending across the open annular space and connecting the first ring and the second ring, where the at least one orifice is in the second ring and the seal portion is on the first ring.

14. The airfoil assembly as recited in claim 13 , wherein the at least one spoke includes first and second spokes located across from each other on opposed sides of the inner ring.

15. The airfoil assembly as recited in claim 1 , wherein the seal portion is in contact with the first platforms of the first and second ceramic airfoils.

16. A gas turbine engine comprising:

a compressor section;

a combustor; and

a turbine section, the turbine section having an airfoil assembly including,

a first and second ceramic airfoil pieces each having first and second platforms and a hollow airfoil section connecting the first and second platforms,

first and second spars extending through, respectively, the hollow airfoil sections, and

identical first and second seals, each of the first and second seals having a seal body defining first and second orifices and a seal portion between the first and second orifices, the first spar extending through the first orifice of the first seal, the second spar extending through the second orifice of the first seal and also through the first orifice of the second seal such that the first and second seals partially overlap, and the seal portion of the first seal bridging a mate face between the first platforms of the first and second ceramic airfoil pieces.

17. The gas turbine engine as recited in claim 16 , wherein each of the hollow airfoil sections defines a longitudinal direction between inner and outer ends, and the seal portion is longitudinally offset from the at least one orifice.

18. A seal for an airfoil assembly, the seal comprising:

a seal body formed of sheet metal and defining at least one orifice configured to receive a spar there through along a longitudinal direction and a seal portion configured to bridge a mate face between adjacent platforms, wherein the seal portion is longitudinally offset from the at least one orifice wherein the at least one orifice includes first and second orifices, and the seal portion is between the first and second orifices.

19. The seal as recited in claim 18 , wherein the seal body defines a first, outer ring; a second, inner ring; and at least one spoke connecting the first ring and the second ring, where the at least one orifice is in the second ring and the seal portion is on the first ring.