Airfoil endwall with partial integral airfoil wall

1. An airfoil comprising:

an airfoil section defining an airfoil profile;

a first endwall piece including a first cup portion defining a first cavity;

a second endwall piece including a second cup portion defining a second cavity and an airfoil wall portion projecting from the second cup portion, the airfoil wall portion forming a portion of the airfoil profile of the airfoil section, the airfoil wall portion including a border wall that is sloped, the border wall being disposed in the first cavity and partitioning the first cavity into a cooling passage; and

an airfoil piece defining another portion of the airfoil profile, the airfoil piece having first and second ends, the first end being disposed in the first cavity and the second end being disposed in the second cavity such that the airfoil piece is trapped between the first endwall piece and the second endwall piece, wherein at least one of the first cup portion or the second cup portion includes a shoulder supporting the airfoil piece, and the one of the first cup portion or the second cup portion that includes the shoulder additionally includes a rib supporting the airfoil piece.

2. The airfoil as recited in claim 1 , wherein the airfoil piece forms a leading end of the airfoil profile.

3. The airfoil as recited in claim 2 , wherein the airfoil piece is ceramic or ceramic matrix composite.

4. The airfoil as recited in claim 1 , wherein the rib includes a cooling passage.

5. The airfoil as recited in claim 1 , wherein the airfoil piece is hollow.

6. The airfoil as recited in claim 1 , further comprising a fastener securing the first endwall piece and the second endwall piece together.

7. The airfoil as recited in claim 1 , wherein the airfoil wall portion has a lip that is bottomed out in the first cavity.

8. The airfoil as recited in claim 1 , wherein the airfoil wall portion includes a shoulder that abuts the first endwall piece such that an exterior airfoil surface of the airfoil wall portion is substantially flush with an exterior endwall surface of the first endwall piece.

9. The airfoil as recited in claim 1 , further comprising a spring adjacent the airfoil piece and disposed in at least one of the first cavity or the second cavity.

10. The airfoil as recited in claim 1 , wherein the border wall is situated opposite a trunnion through which cooling air is provided into the first cavity such that the cooling air impinges upon the border wall.

11. The airfoil as recited in claim 10 , wherein the border wall deflects cooling air toward a leading end of the airfoil section.

12. The airfoil as recited in claim 11 , wherein the rib includes a cooling hole and is situated forward of the border wall to receive the deflected cooling air.

13. The airfoil as recited in claim 12 , wherein the cooling hole in the rib opens into a forward sub-cavity of the first cavity, and the forward sub-cavity opens into an internal passage in the airfoil piece.

14. 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,

at least one of the turbine section or the compressor section including an airfoil having

an airfoil section defining an airfoil profile,

a first endwall piece including a first cup portion defining a first cavity,

a second endwall piece including a second cup portion defining a second cavity and an airfoil wall portion projecting from the second cup portion, the airfoil wall portion forming a portion of the airfoil profile of the airfoil section, the airfoil wall portion including a border wall that is sloped, the border wall being disposed in the first cavity and partitioning the first cavity into a cooling passage, and

an airfoil piece defining another portion of the airfoil profile, the airfoil piece having first and second ends, the first end being disposed in the first cavity and the second end being disposed in the second cavity such that the airfoil piece is trapped between the first endwall piece and the second endwall piece, wherein at least one of the first cup portion or the second cup portion includes a shoulder supporting the airfoil piece, and the one of the first cup portion or the second cup portion that includes the shoulder additionally includes a rib supporting the airfoil piece.

15. The gas turbine engine as recited in claim 14 , wherein the airfoil piece forms a leading end of the airfoil profile.

16. The gas turbine engine as recited in claim 14 , wherein the airfoil wall portion has a lip that is bottomed out in the first cavity.

17. The gas turbine engine as recited in claim 16 , wherein the airfoil wall portion includes a shoulder that abuts the first endwall piece such that an exterior airfoil surface of the airfoil wall portion is substantially flush with an exterior endwall surface of the first endwall piece.

18. An airfoil article comprising:

an endwall piece including a cup portion defining a cavity and an airfoil wall portion projecting from the cup portion, the airfoil wall portion forming a portion of an airfoil profile, wherein the cup portion includes a shoulder and a rib for supporting an airfoil piece received into the cup portion, the airfoil wall portion including a border wall that is sloped, the border wall being disposed in the cavity and partitioning the cavity into a cooling passage.

19. The airfoil article as recited in claim 18 , wherein the airfoil wall portion forms a suction side or a pressure side of the airfoil profile.

20. The airfoil article as recited in claim 19 , wherein the airfoil wall portion excludes a leading end of the airfoil profile.