Composite airfoil assembly with separate airfoil, inner band, and outer band

1. An airfoil assembly for a gas turbine engine, comprising:

an airfoil having a concave pressure side opposite a convex suction side and an inner end spaced apart from an outer end along a radial direction, the pressure side and the suction side extending along an axial direction from a leading edge to a trailing edge, the airfoil defining a cavity, the airfoil including a trailing edge portion located aft of the cavity and defining the trailing edge;

an inner band defining an inner opening shaped complementary to the inner end of the airfoil;

an outer band defining an outer opening shaped complementary to the outer end of the airfoil;

a strut extending along the radial direction through the cavity; and

a first pad defined at a first radial location within the cavity and a second pad defined at a second radial location within the cavity, the first radial location different from the second radial location,

wherein the inner end of the airfoil is received with the inner opening and the outer end of the airfoil is received within the outer opening,

wherein a first slot extending longitudinally along the radial direction is defined in the trailing edge portion for receipt of a first pin, and

wherein each of the inner band, outer band, and airfoil are formed from a ceramic matrix composite material.

2. The airfoil assembly of claim 1 , wherein a second slot extending along the radial direction is defined in the airfoil for receipt of a second pin.

3. The airfoil assembly of claim 2 , wherein the first slot is defined in the outer end of the airfoil and the second slot is defined in the inner end of the airfoil,

wherein a first aperture is defined in an outer support structure such that the first pin passes through the first aperture into the first slot, and

wherein a second aperture is defined in an inner support structure such that the second pin passes through the second aperture into the second slot.

4. The airfoil assembly of claim 1 , wherein the inner band includes a first flowpath surface, a first non-flowpath surface opposite the first flowpath surface, and a first inner flange and a second inner flange extending along the radial direction from the first non-flowpath surface, and

wherein the outer band includes a second flowpath surface, a second non-flowpath surface opposite the second flowpath surface, and a first outer flange and a second outer flange extending along the radial direction from the second non-flowpath surface.

5. The airfoil assembly of claim 4 , wherein the inner band is secured to an inner support structure by a first inner fastener extending through the first inner flange and a second inner fastener extending through the second inner flange, and

wherein the outer band is secured to an outer support structure by a first outer fastener extending through the first outer flange and a second outer fastener extending through the second outer flange.

6. The airfoil assembly of claim 5 , wherein the first inner flange and the second inner flange extend from the first non-flowpath surface of the inner band such that the first inner flange and the second inner flange straddle the inner support structure, and

wherein the first outer flange and the second outer flange extend from the second non-flowpath surface of the outer band such that the first outer flange and the second outer flange straddle the outer support structure.

7. An airfoil assembly for a gas turbine engine, comprising:

an airfoil having a concave pressure side opposite a convex suction side and an inner end spaced apart from an outer end along a radial direction, the pressure side and the suction side extending along an axial direction from a leading edge to a trailing edge, the airfoil including a trailing edge portion defining the trailing edge;

an inner band defining an inner opening shaped complementary to the inner end of the airfoil, the inner band including

a first flowpath surface,

a first non-flowpath surface opposite the first flowpath surface, and

a first inner flange extending along a radial direction from the first non-flowpath surface adjacent an axial mid-portion of the inner band; and

an outer band defining an outer opening shaped complementary to the outer end of the airfoil, the outer band including

a second flowpath surface,

a second non-flowpath surface opposite the second flowpath surface, and

a first outer flange extending along the radial direction from the second non-flowpath surface,

wherein the inner end of the airfoil is received with the inner opening and the outer end of the airfoil is received within the outer opening,

wherein a first slot extending longitudinally along the radial direction is defined in the trailing edge portion for receipt of a first pin, and

wherein the inner band is secured to an inner support structure by a first inner fastener extending through the first inner flange and the outer band is secured to an outer support structure by a first outer fastener extending through the first outer flange.

8. The airfoil assembly of claim 7 , wherein the first outer flange extends from the second non-flowpath surface of the outer band adjacent an aft end of the outer band.

9. The airfoil assembly of claim 7 , wherein the inner band includes a second inner flange extending along the radial direction from the first non-flowpath surface, and

wherein the outer band includes a second outer flange extending along the radial direction from the second non-flowpath surface.

10. The airfoil assembly of claim 9 , wherein the inner band is secured to the inner support structure by a first inner fastener extending through the first inner flange and a second inner fastener extending through the second inner flange, and

wherein the outer band is secured to the outer support structure by a first outer fastener extending through the first outer flange and a second outer fastener extending through the second outer flange.

11. The airfoil assembly of claim 9 , wherein the second inner flange extends from the first non-flowpath surface of the inner band adjacent a forward end of the inner band,

wherein the first outer flange extends from the second non-flowpath surface of the outer band adjacent an aft end of the outer band, and

wherein the second outer flange extends from the second non-flowpath surface of the outer band adjacent a forward end of the outer band.

12. The airfoil assembly of claim 9 , wherein the first inner flange and the second inner flange extend from the first non-flowpath surface of the inner band such that the first inner flange and the second inner flange straddle the inner support structure, and

wherein the first outer flange and the second outer flange extend from the second non-flowpath surface of the outer band such that the first outer flange and the second outer flange straddle the outer support structure.

13. The airfoil assembly of claim 7 , further comprising:

a strut extending along the radial direction through a cavity defined by the airfoil; and

a first pad defined at a first radial location within the cavity and a second pad defined at a second radial location within the cavity, the first radial location different from the second radial location,

wherein a second slot extending longitudinally along the radial direction is defined in the airfoil for receipt of a second pin.

14. The airfoil assembly of claim 13 , wherein the first slot is defined in the outer end of the airfoil and the second slot is defined in the inner end of the airfoil,

wherein a first aperture is defined in the outer support structure such that the first pin passes through the first aperture into the first slot, and

wherein a second aperture is defined in the inner support structure such that the second pin passes through the second aperture into the second slot.

15. The airfoil assembly of claim 7 , wherein each of the inner band, outer band, and airfoil are formed from a ceramic matrix composite material.

16. The airfoil assembly of claim 7 , further comprising:

a second airfoil having a concave pressure side opposite a convex suction side and an inner end spaced apart from an outer end along the radial direction, the pressure side and the suction side of the second airfoil extending along the axial direction from a leading edge to a trailing edge,

wherein the airfoil is a first airfoil, wherein the inner opening is a first inner opening and the outer opening is a first outer opening, wherein the inner band further defines a second inner opening shaped complementary to the inner end of the second airfoil and the outer band further defines a second outer opening shaped complementary to the outer end of the second airfoil such that the airfoil assembly is a doublet airfoil assembly having two airfoils received within a single inner band and a single outer band, and wherein each of the inner band, outer band, first airfoil, and second airfoil are separately formed from a ceramic matrix composite material.

17. The airfoil assembly of claim 7 , wherein the airfoil defines a cavity, and wherein the trailing edge portion is located aft of the cavity.

18. An airfoil assembly for a gas turbine engine, comprising:

an airfoil having a concave pressure side opposite a convex suction side and an inner end spaced apart from an outer end along a radial direction, the pressure side and the suction side extending along an axial direction from a leading edge to a trailing edge;

an inner band defining an inner opening shaped complementary to the inner end of the airfoil, the inner band including

a first flowpath surface,

a first non-flowpath surface opposite the first flowpath surface, and

a first inner flange extending along the radial direction from the first non-flowpath surface;

an outer band defining an outer opening shaped complementary to the outer end of the airfoil, the outer band including

a second flowpath surface,

a second non-flowpath surface opposite the second flowpath surface, and

a first outer flange extending along the radial direction from the second non-flowpath surface;

a strut extending along the radial direction through a cavity defined by the airfoil; and

a first pad defined at a first radial location within the cavity and a second pad defined at a second radial location within the cavity, the first radial location different from the second radial location,

wherein the inner end of the airfoil is received with the inner opening and the outer end of the airfoil is received within the outer opening,

wherein the inner band is secured to an inner support structure by a first inner fastener extending through the first inner flange and the outer band is secured to an outer support structure by a first outer fastener extending through the first outer flange,

wherein the airfoil is constrained along the axial direction by a pair of pins, each pin of the pair of pins having a diameter and an axial length, the axial length of each pin of the pair of pins extending along the radial direction into the airfoil, and

wherein each of the inner band, outer band, and airfoil are formed from a ceramic matrix composite material.

19. The airfoil assembly of claim 18 , wherein the strut is formed from a metallic material, and

wherein the airfoil is free to float along the radial direction.

20. The airfoil assembly of claim 18 , wherein the airfoil includes a trailing edge portion located aft of the cavity and defining the trailing edge, and

wherein a slot extending longitudinally along the radial direction is defined in the trailing edge portion for receipt of one pin of the pair of pins.