Auxetic materials and structures for ceramic matrix composite airfoil mandrels
A method of fabricating a ceramic matrix composite component includes fabricating a ceramic preform, the preform comprising a hollow portion with an internal cavity extending along a first axis from a first end to a second end of the hollow portion, supporting the hollow portion with an auxetic mandrel disposed within and the internal cavity and coaxial with the hollow portion, the auxetic mandrel comprising a first mandrel end and a second mandrel end, at least partially densifying the preform with a matrix, and removing the auxetic mandrel from the internal cavity by simultaneously applying a compressive force to each of the first mandrel end and the second mandrel end creating a deformed auxetic mandrel to reduce a cross-sectional profile of the auxetic mandrel along a second axis orthogonal to the first axis, and extracting the deformed auxetic mandrel from the first end of the hollow portion.
1. A method of fabricating a ceramic matrix composite component, the method comprising:
fabricating a ceramic preform, the preform comprising a hollow portion with an internal cavity extending along a first axis from a first end to a second end of the hollow portion;
supporting the hollow portion with an auxetic mandrel disposed within and the internal cavity and coaxial with the hollow portion, the auxetic mandrel comprising a first mandrel end and a second mandrel end;
at least partially densifying the preform with a matrix; and
removing the auxetic mandrel from the internal cavity by:
simultaneously applying a compressive force to each of the first mandrel end and the second mandrel end creating a deformed auxetic mandrel to reduce a cross-sectional profile of the auxetic mandrel along a second axis orthogonal to the first axis; and
extracting the deformed auxetic mandrel from the first end of the hollow portion.
2. The method of claim 1 , wherein the preform is a vane preform, and wherein the hollow portion is an airfoil.
3. The method of claim 2 , wherein the step of fabricating the ceramic preform comprises laying up a ceramic material over the auxetic mandrel.
4. The method of claim 3 , wherein the ceramic material comprises silicon carbide fibers.
5. The method of claim 2 , wherein the auxetic mandrel is formed from graphene.
6. The method of claim 2 , wherein the auxetic mandrel is formed from one of a metal, a polymer, a ceramic, and a composite material.
7. The method of claim 2 , wherein the step of at least partially densifying the preform with a ceramic matrix is carried out using chemical vapor infiltration.
8. The method of claim 2 , wherein the step of at least partially densifying the preform with a ceramic matrix is carried out using polymer infiltration and pyrolysis or melt infiltration.
9. The method of claim 2 , wherein the airfoil comprises:
a first sidewall;
a second sidewall; and
a reduced thickness region therebetween.
10. The method of claim 9 , wherein the auxetic mandrel comprises a flared region corresponding to a flared region of the first sidewall.
11. The method of claim 10 , wherein in the deformed auxetic mandrel, a cross-sectional profile of the flared region of the auxetic mandrel is less than the reduced thickness region of the airfoil.
12. The method of claim 11 , wherein the step of removing the auxetic mandrel from the airfoil comprises moving the flared region of the auxetic mandrel through the reduced thickness region of the airfoil.
13. The method of claim 2 , wherein the compressive force is applied to each of the first mandrel end and the second mandrel end by hand.
14. The method of claim 2 , wherein the compressive force is applied to each of the first mandrel end and the second mandrel end using a tool.
15. The method of claim 14 , wherein the tool is a clamp.