Seal coats to prevent silicon loss during re-melt infiltration of Si containing composites
Provided is a method including obtaining ceramic matrix composite (CMC) with a first matrix portion including a silicon carbide and silicon phase dispersed therewithin, disposing a coating thereupon to form a sealed part, and forming thereupon another segment comprising a CMC, which may be another matrix portion including a silicon carbide and a silicon phase dispersed within therewithin. Also provided is a gas turbine component with a CMC segment including a matrix portion including a silicon carbide and a silicon phase dispersed therewithin, a sealing layer including silicon carbide enclosing the first segment, and a second segment on the sealing layer, wherein the second segment includes a melt-infiltrated CMC having a matrix portion including a silicon carbide and a silicon phase dispersed therewithin.
1. A gas turbine component, comprising:
a first segment comprising a ceramic matrix composite (CMC) including a first matrix portion, wherein the first matrix portion comprises a first silicon carbide and a first silicon phase dispersed within the first silicon carbide;
a sealing layer comprising silicon carbide, wherein the sealing layer encloses the first segment and comprises an external surface, and wherein the sealing layer is nonporous to form a complete barrier between the first silicon phase of the first segment and the sealing layer; and
a second segment on the external surface of the sealing layer, wherein the second segment comprises a melt-infiltrated CMC having a second matrix portion and the second matrix portion comprises a second silicon carbide and a second silicon phase dispersed within the second silicon carbide.
2. The gas turbine component of claim 1 , wherein the gas turbine component comprises a blade.
3. A gas turbine comprising the gas turbine component of claim 1 .
4. The gas turbine component of claim 1 , wherein the sealing layer is configured to minimize wicking of the first silicon phase.
5. The gas turbine component of claim 1 , wherein the sealing layer at least partially fills a portion of the first matrix portion.
6. The gas turbine component of claim 1 , wherein a first coefficient of thermal expansion of the sealing layer is substantially similar to a second coefficient of thermal expansion of the first segment, a third coefficient of thermal expansion of the second segment, or both.
7. The gas turbine component of claim 1 , wherein the sealing layer encloses substantially all external surfaces of the first segment.
8. The gas turbine component of claim 1 , wherein the gas turbine component comprises a vane.
9. The gas turbine component of claim 1 , wherein the gas turbine component comprises a nozzle.
10. The gas turbine component of claim 1 , wherein the gas turbine component comprises a shroud.
11. The gas turbine component of claim 1 , wherein the gas turbine component comprises a combustor liner.
12. The gas turbine component of claim 1 , wherein the gas turbine component comprises a center frame.
13. The gas turbine component of claim 1 , wherein the gas turbine component is a repaired gas turbine component formed from an originally manufactured gas turbine component having the first segment.
14. The gas turbine component of claim 1 , wherein the sealing layer comprises a material formed by carburization or nitriding of a surface of the first segment.
15. The gas turbine component of claim 1 , wherein the ceramic matrix composite of the first segment includes first fibers within the first matrix portion, and wherein the melt-infiltrated CMC of the second segment comprises second fibers within the second matrix portion.
16. A gas turbine component, comprising:
a first segment comprising a ceramic matrix composite (CMC) including a first matrix portion, wherein the first matrix portion comprises a first silicon carbide and a first silicon phase dispersed within the first silicon carbide;
a sealing layer comprising a material formed by carburization or nitriding of a surface of the first segment, wherein the sealing layer encloses the first segment and comprises an external surface, and wherein the sealing layer is nonporous to form a complete barrier between the first silicon phase of the first segment and the sealing layer; and
a second segment on the external surface of the sealing layer, wherein the second segment comprises a melt-infiltrated CMC having a second matrix portion and the second matrix portion comprises a second silicon carbide and a second silicon phase dispersed within the second silicon carbide.
17. The gas turbine component of claim 16 , wherein the material of the sealing layer is silicon carbide, silicon nitride, or boron carbide.
18. The gas turbine component of claim 16 , wherein the sealing layer is configured to minimize wicking of the first silicon phase.