Composite turbine vane with three-dimensional fiber reinforcements

1. A turbine vane made from ceramic matrix composite material and adapted for use in a gas turbine engine, the turbine vane comprising

an inner band configured to define a circumferentially extending inner flow path surface;

an outer band configured to define a circumferentially extending outer flow path surface; and

an airfoil that extends from the inner band to the outer band across a flow path defined between the inner flow path surface and the outer flow path surface,

wherein the turbine vane includes three-dimensionally woven reinforcement fibers suspended in matrix material, the three-dimensionally woven reinforcement fibers including a plurality of tows each shaped to provide at least a portion of the inner band, the outer band, and the airfoil, the plurality of tows including a first plurality of fibers arranged generally in a hoop direction from a pressure side to a suction side of the airfoil and a second plurality of fibers woven with the first plurality of fibers and arranged in at least one of a radial direction, an axial direction, and a circumferential direction, the radial direction, the axial direction, and the circumferential direction each being different than the hoop direction, and wherein the airfoil has a higher fraction of the first plurality of fibers that extend in the hoop direction compared to fibers that extend in any one of the radial direction, the axial direction, and the circumferential direction,

wherein the airfoil includes a primary airfoil portion made at least in part from the three-dimensionally woven reinforcement fibers and the three-dimensionally woven fiber reinforcements of the primary airfoil portion are shaped to provide a leading end, a trailing end, a pressure side wall, and a suction side wall spaced apart from the pressure side wall to define a cooling cavity within the primary airfoil portion between the leading end, the trailing end, the pressure side wall, and the suction side wall,

wherein the airfoil includes a trailing-edge insert coupled to the primary airfoil portion to define a trailing edge of the airfoil, and

wherein the trailing edge insert includes an interior portion that extends into the cooling cavity and an exterior portion that defines the trailing-edge of the airfoil.

2. The turbine vane of claim 1 , wherein the three-dimensionally woven fiber reinforcements of the primary airfoil portion are shaped to provide a rib that extends from the pressure side wall to the suction side wall through the cooling cavity.

3. The turbine vane of claim 2 , wherein the rib is interrupted between the radially inner band and the radially outer band such that spaces are formed between portions of the rib.

4. The turbine vane of claim 1 , wherein the trailing-edge insert extends into recesses formed in the inner band and the outer band to couple the trailing-edge insert to the primary airfoil portion.

5. The turbine vane of claim 1 , wherein the trailing-edge insert comprises one of monolithic ceramic material and ceramic matrix composite material; and the trailing-edge insert is coupled to the primary airfoil portion by matrix material.

6. The turbine vane of claim 5 , wherein the interior portion includes bonding surfaces that engage inner surfaces defining the cooling cavity of the primary airfoil portion.

7. The turbine vane of claim 5 , wherein the interior portion includes bonding surfaces that face inner surfaces defining the cooling cavity of the primary airfoil portion and the matrix material is disposed on the bonding surfaces and the inner surfaces to bond the trailing edge insert to the primary airfoil portion.

8. The turbine vane of claim 1 , wherein at least one of the inner band and the outer band has a higher fraction of the second plurality of fibers that extend in the circumferential direction compared to fibers that extend in any one of the radial direction and axial direction.

9. The turbine vane of claim 1 , wherein the first plurality of fibers that extend in the hoop direction are generally perpendicular to the radial direction.

10. A turbine vane made from ceramic matrix composite material and adapted for use in a gas turbine engine, the turbine vane comprising

an inner band configured to define a circumferentially extending inner flow path surface;

an outer band configured to define a circumferentially extending outer flow path surface; and

an airfoil that extends from the inner band to the outer band across a flow path defined between the inner flow path surface and the outer flow path surface,

wherein the turbine vane includes three-dimensionally woven reinforcement fibers suspended in matrix material, the three-dimensionally woven reinforcement fibers including a plurality of tows each shaped to provide at least a portion of the inner band, the outer band, and the airfoil, the plurality of tows including a first plurality of fibers arranged generally in a hoop direction from a pressure side to a suction side of the airfoil and a second plurality of fibers woven with the first plurality of fibers and arranged in at least one of a radial direction, an axial direction, and a circumferential direction, the radial direction, the axial direction, and the circumferential direction each being different than the hoop direction, and wherein the airfoil has a higher fraction of the first plurality of fibers that extend in the hoop direction compared to fibers that extend in any one of the radial direction, the axial direction, and the circumferential direction,

wherein the airfoil includes a primary airfoil portion made at least in part from the three-dimensionally woven reinforcement fibers and the three-dimensionally woven fiber reinforcements of the primary airfoil portion are shaped to provide a pressure side wall and a suction side wall spaced apart from the pressure side wall to define a cooling cavity therebetween,

wherein the airfoil includes a trailing-edge insert coupled to the primary airfoil portion to define a trailing edge of the airfoil, and

wherein the trailing-edge insert is formed to include cooling air discharge apertures that open into the cooling cavity to carry cooling air from inside the airfoil axially-aft out to the gas path.

11. A turbine vane made from ceramic matrix composite material and adapted for use in a gas turbine engine, the turbine vane comprising

an inner band configured to define a circumferentially extending inner flow path surface, the inner band including three-dimensionally woven reinforcement fibers;

an outer band configured to define a circumferentially extending outer flow path surface, the outer band including three-dimensionally woven reinforcement fibers; and

an airfoil that extends from the inner band to the outer band across a flow path defined between the inner flow path surface and the outer flow path surface, the airfoil including three-dimensionally woven reinforcement fibers,

wherein the three-dimensionally woven reinforcement fibers included in the airfoil include a plurality of tows each shaped to provide at least a portion of the inner band and the outer band, the plurality of tows including a first plurality of fibers arranged generally in a hoop direction from a pressure side to a suction side of the airfoil and a second plurality of fibers woven with the first plurality of fibers and arranged in at least one of a radial direction, an axial direction, and a circumferential direction, the radial direction, the axial direction, and the circumferential direction each being different than the hoop direction, and wherein the airfoil has a higher fraction of the first plurality of fibers that extend in the hoop direction compared to fibers that extend in any one of the radial direction, the axial direction, and the circumferential direction.

12. The turbine vane of claim 11 , wherein the airfoil includes a trailing-edge insert coupled to a primary airfoil portion that includes the three-dimensionally woven reinforcement such that the trailing-edge insert defines a trailing edge of the airfoil.

13. The turbine vane of claim 12 , wherein the trailing-edge insert is formed to include cooling air discharge apertures in fluid communication with a cooling cavity formed by the primary airfoil portion to carry cooling air from inside the airfoil out to the gas path.

14. The turbine vane of claim 12 , wherein the trailing-edge insert extends into recesses formed in the inner band and the outer band to couple the trailing-edge insert to the primary airfoil portion.

15. The turbine vane of claim 12 , wherein the trailing-edge insert comprises one of monolithic ceramic material and ceramic matrix composite material; and the trailing-edge insert is coupled to the primary airfoil portion by matrix material.

16. The turbine vane of claim 11 , wherein the airfoil includes a primary airfoil portion made at least in part from the three-dimensionally woven reinforcement fibers and the three-dimensionally woven fiber reinforcements of the primary airfoil portion are shaped to provide a leading end, a trailing end, a pressure side wall, and a suction side wall spaced apart from the pressure side wall to define a cooling cavity between the leading end, the trailing end, the pressure side wall, and the suction side wall, wherein the airfoil includes a trailing-edge insert coupled to the primary airfoil portion to define a trailing edge of the airfoil, and wherein the trailing edge insert includes an interior portion that extends into the cooling cavity and an exterior portion that defines the trailing-edge of the airfoil.

17. The turbine vane of claim 16 , wherein the interior portion includes bonding surfaces that engage inner surfaces defining the cooling cavity of the primary airfoil portion.

18. The turbine vane of claim 16 , wherein the interior portion includes bonding surfaces that face inner surfaces defining the cooling cavity of the primary airfoil portion and matrix material is disposed on the bonding surfaces and the inner surfaces to bond the trailing edge insert to the primary airfoil portion.

19. The turbine vane of claim 11 , wherein at least one of the inner band and the outer band has a higher fraction of the second plurality of fibers that extend in the circumferential direction compared to fibers that extend in any one of the radial direction and axial direction.

20. The turbine vane of claim 11 , wherein the first plurality of fibers that extend in the hoop direction are generally perpendicular to the radial direction.