Molybdenum-silicon-boron with noble metal barrier layer
An article includes a substrate formed of a molybdenum-based alloy. The molybdenum-based alloy has a composition that includes molybdenum, silicon, and boron. A barrier layer is disposed on the substrate. The barrier layer is formed of at least one noble metal.
1. An article comprising:
a substrate formed of a molybdenum-based alloy, the molybdenum-based alloy having a composition including molybdenum, silicon, and boron;
a barrier layer disposed on the substrate, the barrier layer formed of at least one noble metal; and
a metal interlayer disposed between the substrate and the barrier layer.
2. The article as recited in claim 1 , wherein the metal interlayer is formed of a different metal than the barrier layer and is selected from the group consisting of copper, gold, platinum, and combinations thereof.
3. The article as recited in claim 1 , wherein the metal interlayer includes copper.
4. The article as recited in claim 1 , wherein the at least one noble metal is selected from the group consisting of ruthenium, rhodium, palladium, silver, osmium, iridium, platinum, gold, and combinations thereof.
5. The article as recited in claim 1 , wherein the at least one noble metal includes platinum.
6. The article as recited in claim 1 , further comprising a topcoat disposed on the barrier layer.
7. The article as recited in claim 6 , wherein the topcoat is formed of a silica material.
8. The article as recited in claim 1 , wherein the substrate defines an internal cavity, and the barrier layer is disposed on the substrate in the internal cavity.
9. A method of fabricating an article, the method comprising:
depositing a barrier layer onto a substrate formed of a molybdenum-based alloy, the molybdenum-based alloy having a composition that includes molybdenum, silicon, and boron, and the barrier layer having at least one noble metal; and
prior to depositing the barrier layer, depositing a metal interlayer onto the substrate.
10. The method as recited in claim 9 , wherein the metal interlayer is formed of a different metal than the barrier layer and is selected from the group consisting of copper, gold, platinum, and combinations thereof.
11. The method as recited in claim 10 , further comprising thermally treating the substrate with the metal interlayer and the barrier layer, and conducting the thermal treating at a temperature above the melting point of the metal of the metal interlayer but below the melting point of the at least one noble metal.
12. The method as recited in claim 9 , including depositing the metal interlayer and depositing the barrier layer using electroplating.
13. The method as recited in claim 9 , wherein the substrate defines an internal cavity, and the barrier layer is deposited on the substrate in the internal cavity.
14. A gas turbine engine comprising:
at least one an engine section, the at least one engine section selected from the group consisting of a compressor section, a combustor section, and a turbine section, the at least one engine section having a turbine engine component including,
a substrate formed of a molybdenum-based alloy, the molybdenum-based alloy having a composition including molybdenum, silicon and boron;
a barrier layer disposed on the substrate, the barrier layer formed of at least one noble metal; and
a metal interlayer disposed between the substrate and the barrier layer.
15. The gas turbine engine as recited in claim 14 , wherein the metal interlayer is formed of a different metal than the barrier layer and is selected from the group consisting of copper, gold, platinum, and combinations thereof.
16. The gas turbine engine as recited in claim 14 , wherein the at least one noble metal is selected from the group consisting of ruthenium, rhodium, palladium, silver, osmium, iridium, platinum, gold, and combinations thereof.
17. A gas turbine engine comprising:
at least one engine section, the at least one engine section selected from the group consisting of a compressor section, a combustor section, and a turbine section, the at least one engine section having a turbine engine component including,
a substrate formed of a molybdenum-based alloy, the molybdenum-based alloy having a composition including molybdenum, silicon, and boron, and
a barrier layer disposed on the substrate, the barrier layer formed of at least one noble metal;
wherein the substrate defines an internal cavity, and the metal interlayer and the barrier layer are disposed on the substrate in the internal cavity.