Through thickness reinforcement
A method for making a ceramic matrix composite component includes densifying a fibrous preform of the component with a ceramic matrix to form an intermediate component; infiltrating a hole in the intermediate component with an infiltrate material comprising a solid and a metallic alloy whose reaction forms a carbide, silicide, boride or combination thereof, heating the infiltrate material to a temperature in excess of a melting point of the metallic alloy; and sequentially cooling regions of the hole starting from an interior end of the hole to the outer surface of the intermediate component to form a solidified through-thickness reinforcement element. The hole extends in a through-thickness direction and is open to an exterior surface of the intermediate component.
1. A method for making a ceramic matrix composite component, the method comprising:
densifying a fibrous preform of the component with a ceramic matrix to form an intermediate component;
infiltrating a hole in the intermediate component with an infiltrate material comprising a molten silicon-based metallic alloy and a solid whose reaction forms a carbide, silicide, boride or combination thereof, wherein the hole extends in a through-thickness direction and is open to an outer surface of the intermediate component;
heating the infiltrate material to a temperature in excess of a melting point of the silicon-based metallic alloy to remelt the silicon-based metallic alloy; and
sequentially cooling regions of the hole starting from an interior end of the hole to the outer surface of the intermediate component to form a solidified through-thickness reinforcement element, wherein sequential cooling follows heating the infiltrate material;
wherein residual unreacted silicon remains in the hole following infiltrating a hole in the intermediate component with the infiltrate material, and wherein the unreacted residual silicon is melted when the infiltrate material is heated and moves outward through the hole toward the outer surface during sequential cooling.
2. The method of claim 1 , wherein sequentially cooling regions of the hole comprises moving the intermediate component through a temperature gradient.
3. The method of claim 2 , wherein sequentially cooling regions of the heated hole results in recrystallization of the infiltrate material.
4. The method of claim 3 , wherein an average crystal size of the solidified through-thickness reinforcement element is greater than an average crystal size of the ceramic matrix.
5. The method of claim 3 , wherein the through-thickness reinforcement element is a polycrystalline, eutectic, or single crystal ceramic.
6. The method of claim 2 , wherein the infiltrate material comprises a carbon source, and wherein the silicon-based metallic alloy reacts with the carbon source to form silicon carbide when the infiltrate material is heated to a temperature in excess of a melting point of the silicon-based metallic alloy.
7. The method of claim 6 , wherein infiltrating the hole comprises infiltrating with a slurry containing the carbon source to deposit the carbon source in the hole.
8. The method of claim 1 , wherein infiltrating the hole comprises depositing a carbon source on a surface of the hole via a vapor phase deposition process.
9. The method of claim 1 , wherein the infiltrate material comprises aluminum, boron, chromium, hafnium, iron, molybdenum, niobium, rare earth metals, scandium, tantalum, titanium, tungsten, vanadium, yttrium, zirconium, or a combination thereof.
10. The method of claim 1 , and further comprising depositing a carbon source on the outer surface of the intermediate component.
11. The method of claim 1 , and further comprising forming the hole in the fibrous preform.
12. The method of claim 1 , and further comprising depositing an interphase coating on surfaces of the hole.
13. The method of claim 1 , wherein the residual silicon reacts with a carbon source provided on the outer surface of the intermediate component.