Ceramic component having silicon layer and barrier layer
A seal system includes a ceramic component, a metallic component, a coating system. The ceramic component has a first surface region that defines a first surface roughness. The metallic component is situated adjacent to the first surface region and has a second surface region facing the first surface region. The coating system includes a silicon-containing layer on the surface region of the ceramic component and barrier layer on the silicon-containing layer. The silicon containing layer has a surface in contact with the barrier layer and the barrier layer has a surface in contact with the metallic component. The surface of the barrier layer has a second surface roughness that is less than the first surface roughness. The barrier layer serves to limit interaction between silicon of the silicon-containing layer and elements of the metallic component. The barrier layer includes at least one of mullite, zircon, or hafnon.
1. A seal system comprising:
a ceramic component having a surface region defining a first surface roughness;
a metallic component situated adjacent the surface region; and
a coating system disposed on the surface region, the coating system including a silicon-containing layer on the surface region and a barrier layer on the silicon-containing layer, the silicon-containing layer having a surface in contact with the barrier layer, the barrier layer having a surface in contact with the metallic component, the surface of the barrier layer having a second surface roughness that is less than the first surface roughness, the barrier layer limiting interaction between silicon of the silicon-containing layer and elements of the metallic component, and the barrier layer including at least one of mullite, zircon, or hafnon.
2. The seal system as recited in claim 1 , wherein the barrier layer is selected from the group consisting of mullite, zircon, and hafnon, and the metallic component is a nickel- or cobalt-based superalloy.
3. The seal system as recited in claim 2 , wherein the barrier layer is mullite.
4. The seal system as recited in claim 2 , wherein the barrier layer is zircon.
5. The seal system as recited in claim 2 , wherein the barrier layer is hafnon.
6. The seal system as recited in claim 2 , wherein the silicon-containing layer is silicon.
7. The seal system as recited in claim 1 , wherein the silicon-containing layer is silicon.
8. A gas turbine engine comprising:
a compressor section;
a combustor in fluid communication with the compressor section; and
a turbine section in fluid communication with the combustor, and at least one sealing system in the turbine section or the combustor, the sealing system including:
a ceramic component having a surface region defining a first surface roughness,
a metallic component situated adjacent the surface region, and
a coating system disposed on the surface region, the coating system including a silicon-containing layer on the surface region and a barrier layer on the silicon-containing layer and in contact with the metallic component, the silicon-containing layer having a surface in contact with the barrier layer, the barrier layer having a surface in contact with the metallic component, the surface of the barrier layer having a second surface roughness that is less than the first surface roughness, the barrier layer limiting interaction between silicon of the silicon-containing layer and elements of the metallic component, and the barrier layer including at least one of mullite, zircon, or hafnon.
9. The gas turbine engine as recited in claim 8 , wherein the barrier layer is selected from the group consisting of mullite, zircon, and hafnon, and the metallic component is a nickel- or cobalt-based superalloy.
10. The gas turbine engine as recited in claim 9 , wherein the barrier layer is mullite.
11. The gas turbine engine as recited in claim 9 , wherein the barrier layer is zircon.
12. The gas turbine engine as recited in claim 9 , wherein the barrier layer is hafnon.
13. The gas turbine engine as recited in claim 9 , wherein the silicon-containing layer is silicon.
14. The gas turbine engine as recited in claim 8 , wherein the silicon-containing layer is silicon.