Machinable CMC insert

1. A component for use in a gas turbine engine, the component comprising:

a structural component comprising silicon carbide fibers within a silicon carbide matrix, and

a sacrificial layer joined to the structural component comprising unarranged ceramic fibers,

wherein the sacrificial layer comprises a volume fiber fraction lower than a volume fiber fraction of the structural component, and

wherein the sacrificial layer and the structural component are co-infiltrated with silicon metal that joins the structural component and the sacrificial layer.

2. The component of claim 1 , wherein the unarranged ceramic fibers of the sacrificial layer comprise chopped fibers, loosely braided fibers, or a combination thereof.

3. The component of claim 2 , wherein the sacrificial layer comprises a needle punched layer.

4. The component of claim 1 , wherein the sacrificial layer comprises a machined layer.

5. The component of claim 1 , wherein the unarranged ceramic fibers of the sacrificial layer are substantially uncoated.

6. The component of claim 1 , wherein an architecture of the structural component comprises a 2D laminate, a 3D weave, or any other composite architecture.

7. The component of claim 6 , wherein the 2D laminate comprises a plurality of woven layers of silicon carbide fibers.

8. The component of claim 6 , wherein the silicon carbide fibers of the structural component further comprise a coating selected from the group consisting of boron nitride, pyrolitic carbon, oxide interface coating, or a combination thereof.

9. The component of claim 1 , wherein the structural component comprises a blade track, a blade, a vane, a combustor, a combustor tile, a faring, an exhaust tail cone, exhaust liner flaps, or a combination thereof.

10. The component of claim 9 , wherein the structural component is a blade track, wherein the sacrificial layer at least partially wraps around the structural component, and wherein the sacrificial layer is located along an attachment arm of the blade track.

11. The component of claim 9 , wherein the structural component is a blade, and wherein the sacrificial layer surrounds an exterior wall of the blade.

12. The component of claim 9 , wherein the structural component is a vane, and wherein the sacrificial layer surrounds an exterior wall or inner wall of the vane.

13. The component of claim 1 , wherein the sacrificial layer is between about 0.005 inches and about 0.04 inches thick.

14. The component of claim 1 , wherein the unarranged ceramic fibers of the sacrificial layer are substantially devoid of a boron nitride containing coating.

15. A method of forming an insert for use in a gas turbine engine, the method comprising:

forming silicon carbide fibers into a substantially woven pattern to create a structural component;

at least partially covering the structural component with a sacrificial layer comprising unarranged ceramic fibers; and

infiltrating the structural component and the sacrificial layer with silicon metal to join the structural layer and the sacrificial layer,

wherein the sacrificial layer includes a volume fiber fraction less than a volume fiber fraction of the structural component.

16. The method of claim 15 , wherein at least partially covering the structural component with the sacrificial layer comprises wrapping at least one side of the structural component.

17. The method of claim 15 , further comprising chopping ceramic fibers to form the unarranged ceramic fibers.

18. The method of claim 15 , further comprising needle punching the sacrificial layer.

19. The method of claim 15 , wherein infiltrating the structural component and the sacrificial layer comprises chemical vapor deposition, slurry infiltration, melt infiltration, or a combination thereof, and wherein silicon metal comprises a silicon alloy.

20. The method of claim 15 , further comprising machining the sacrificial layer is machined to a final shape without exposing the structural component to an environment.