CERAMIC MATRIX COMPOSITE COMPONENT HAVING LOW DENSITY CORE AND METHOD OF MAKING
Disclosed is a ceramic matrix component having a fibrous core and a ceramic matrix composite shell surrounding at least a portion of the fibrous core. The fibrous core has a three dimensional braided structure and cooling passages. A method of making the ceramic matrix component is also disclosed.
1 . A ceramic matrix component having a fibrous core and a ceramic matrix composite shell surrounding at least a portion of the fibrous core wherein the fibrous core has a three dimensional braided structure and cooling passages.
2 . The ceramic matrix component of claim 1 , wherein the ceramic matrix component is an airfoil.
3 . The ceramic matrix component of claim 2 , wherein the airfoil has a root and the core has cooling passages in the root portion.
4 . The ceramic matrix component of claim 2 , wherein the cooling passages are located in a radial direction.
5 . The ceramic matrix component of claim 2 , wherein the cooling passages in the fibrous core terminate at a leading edge.
6 . The ceramic matrix component of claim 2 , wherein the cooling passages in the fibrous core terminate at the trailing edge.
7 . The ceramic matrix component of claim 2 , wherein the cooling passages in the fibrous core connect to passages in the ceramic matrix composite shell.
8 . The ceramic matrix component of claim 1 , wherein the fibrous core further comprises a ceramic foam.
9 . The ceramic matrix component of claim 8 , wherein the ceramic foam is present at a leading edge, a trailing edge or both.
10 . The ceramic matrix component of claim 1 , wherein the component is a combustor component, vane, blade, vanes, ceramic box shroud, or nozzle component.
11 . A method of making a ceramic matrix component comprising forming a fibrous core having a three dimensional braided structure with carbon and ceramic fibers, partially densifying the fibrous core, pyrolyzing the carbon fibers to form passages, forming a fibrous preform on the partially densified fibrous core, and forming a ceramic matrix on the fibrous preform using chemical vapor infiltration.
12 . The method of claim 11 , wherein the ceramic matrix component is an airfoil.
13 . The method of claim 12 , wherein the passages are located in a radial direction.
14 . The method of claim 12 , wherein the passages in the fibrous core terminate at a leading edge.
15 . The method of claim 12 , wherein the passages in the fibrous core terminate at the trailing edge.
16 . The method of claim 11 , wherein the fibrous core further comprises a ceramic foam.
17 . The method of claim 16 , wherein the ceramic foam is present at a leading edge, a trailing edge or both.
18 . The method of claim 11 , wherein the fibrous core has a porosity greater than the porosity of the fibrous preform.
19 . The method of claim 18 , wherein the porosity of the fibrous core is 2 to 3 times greater than the porosity of the fibrous preform.
20 . The method of claim 11 , wherein the component is a combustor component, vane, blade, vanes, ceramic box shroud, or nozzle component.