Composite turbine vane with three-dimensional fiber reinforcements

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.

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.