Fiber reinforced airfoil
An airfoil and a method of manufacturing an airfoil may be provided, where the airfoil comprises a core and a shell. The core comprises core ceramic fibers extending along a span of the airfoil. The shell surrounds the core and includes shell ceramic fibers. Substantially all of the core ceramic fibers are arranged in a radial direction. The airfoil may also be a ceramic matrix composite formed by infiltrating the core and the shell with a matrix material.
1. An airfoil comprising a unitary ceramic matrix composite (CMC) body, the unitary CMC body comprising:
a core comprising a plurality of core ceramic fibers, wherein substantially all of the plurality of the core ceramic fibers are arranged in a radial direction; and
a shell surrounding the core, the shell comprising a plurality of shell ceramic fibers, wherein a first portion of the shell ceramic fibers are arranged in a first direction substantially aligned with a radial axis of the airfoil, and a second portion of the shell ceramic fibers are arranged to extend along a circumference of the airfoil.
2. The airfoil of claim 1 , wherein the radial direction extends along the airfoil from a base of the airfoil to a tip of the airfoil.
3. The airfoil of claim 1 , wherein at least a portion of the core ceramic fibers comprise a plurality of multi-fiber tows.
4. The airfoil of claim 1 , wherein at least a portion of the core ceramic fibers comprise monofilament.
5. The airfoil of claim 1 , wherein at least a portion of the core ceramic fibers comprise silicon carbide fibers.
6. The airfoil of claim 1 , wherein the plurality of core ceramic fibers have a higher creep resistance than the plurality of shell ceramic fibers.
7. The airfoil of claim 1 , wherein the plurality of core ceramic fibers comprise unidirectional ceramic tape.
8. The airfoil of claim 1 , wherein the shell ceramic fibers are woven or braided.
9. The airfoil of claim 1 , wherein the shell ceramic fibers consists of 2-4 plies of fibers.
10. The airfoil of claim 1 , wherein a surface density of the second portion of the shell ceramic fibers is greater than a surface density of the first portion of the shell ceramic fibers.
11. The airfoil of claim 1 , wherein the second portion of the shell ceramic fibers are angularly offset from a radial axis of the airfoil by between 15 degrees to 75 degrees.
12. The airfoil of claim 1 , wherein a trailing end of the shell comprises a Y-cloth ply.
13. A vane or a blade for a gas turbine engine, the vane or the blade comprising a unitary ceramic matrix composite (CMC) body, the unitary CMC body comprising:
a core comprising a plurality of core ceramic fibers, wherein substantially all of the core ceramic fibers are arranged in a radial direction; and
a shell surrounding the core, the shell comprising a plurality of shell ceramic fibers, wherein a first portion of the shell ceramic fibers are arranged in a first direction substantially aligned with a radial axis of the airfoil, and a second portion of the shell ceramic fibers are arranged to extend along a circumference of the airfoil.
14. The vane or blade of claim 13 , wherein at least 75% of the core ceramic fibers are offset from a radial axis of the blade or vane by no more than 10 degrees.
15. The vane or blade of claim 13 , wherein at least 25% of the shell ceramic fibers extend circumferentially about the shell.
16. A method of manufacturing a ceramic matrix composite (CMC) airfoil comprising:
providing a porous ceramic preform core comprising a plurality of core ceramic fibers by arranging substantially all of the core ceramic fibers in a radial direction;
forming a porous ceramic preform shell to extend around the porous ceramic preform core, the porous ceramic preform shell comprising a plurality of shell ceramic fibers, wherein a first portion of the shell ceramic fibers are arranged in a first direction substantially aligned with a radial axis of the airfoil, and a second portion of the shell ceramic fibers are arranged to extend along a circumference of the airfoil; and
forming the porous ceramic preform core and the porous ceramic preform shell into the CMC airfoil.
17. The method of claim 16 , wherein forming the CMC airfoil comprises infiltrating a molten metal or alloy into the porous ceramic preform core and shell.
18. The method of claim 16 , wherein forming the porous ceramic preform shell comprises wrapping a layer of the shell ceramic fibers around the porous ceramic preform core such that a portion of the layer extends beyond where a trailing edge of CMC airfoil will be after the CMC airfoil is formed.
19. The method of claim 16 , further comprising inserting the core ceramic fibers into the porous ceramic preform shell.
20. The airfoil of claim 1 , wherein a ratio between a diameter of the core ceramic fibers and a diameter of the shell ceramic fibers is at least 2.5.