Molybdenum-silicon-boron with noble metal barrier layer

Patent metadata

Field	Value
Publication number	US-11111797-B2
Application number	US-201916432417-A
Country	US
Kind code	B2
Filing date	Jun 5, 2019
Priority date	May 9, 2016
Publication date	Sep 7, 2021
Grant date	Sep 7, 2021

Abstract

An article includes a substrate formed of a molybdenum-based alloy. A barrier layer is disposed on the substrate. The barrier layer is formed of at least one noble metal.

First claim

What is claimed is:

1. An article comprising:
a substrate formed of a molybdenum-based alloy;
a barrier layer immediately adjacent to and contiguous with the substrate, the barrier layer formed of at least one noble metal, and
a topcoat disposed on the barrier layer, wherein the topcoat includes a silica material and molybdenum silicide.

2. 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.

3. The article as recited in claim 1 , wherein the at least one noble metal includes platinum.

4. 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.

5. The article as recited in claim 1 , wherein the barrier layer has a thickness of between 1 micrometer and about 50 micrometers.

6. The article as recited in claim 1 , wherein the molybdenum-based alloy includes at least 0.2% by weight of alloying elements, and the balance molybdenum.

7. The article as recited in claim 6 , wherein the alloying elements include silicon and boron.

8. A method of fabricating an article, the method comprising:
depositing a barrier layer onto a substrate formed of a molybdenum-based alloy, the barrier layer having at least one noble metal; and
depositing a topcoat on the barrier layer, wherein the topcoat includes a silica material and molybdenum silicide.

9. The method as recited in claim 8 , wherein the depositing is by electroplating.

10. The method as recited in claim 8 , wherein the substrate defines an internal cavity, and the barrier layer is deposited on the substrate in the internal cavity.

11. The method as recited in claim 8 , wherein the barrier layer has a thickness of between 1 micrometer and about 50 micrometers after the depositing.

12. The method as recited in claim 8 , wherein the molybdenum-based alloy includes at least 0.2% by weight of alloying elements, and the balance molybdenum.

13. The method as recited in claim 12 , wherein the alloying elements include silicon and boron.

14. A gas turbine engine section comprising:
an engine section selected from the group consisting of a compressor section, a combustor section, and a turbine section, the engine section having a turbine engine component including,
a substrate formed of a molybdenum-based alloy,
a barrier layer disposed on the substrate, the barrier layer formed of at least one noble metal, and
a topcoat disposed on the barrier layer, wherein the topcoat includes a silica material and molybdenum silicide.

15. The gas turbine engine section 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.

16. The gas turbine engine section as recited in claim 14 , wherein the substrate defines an internal cavity, and the metal interlayer and the barrier layer are disposed on the substrate in the internal cavity.

17. The gas turbine engine section as recited in claim 14 , wherein the barrier layer has a thickness of between 1 micrometer and about 50 micrometers after the depositing.

18. The gas turbine engine section as recited in claim 14 , wherein the molybdenum-based alloy includes at least 0.2% by weight of alloying elements, and the balance molybdenum.

Assignees

• Raytheon Tech Corp

Inventors

• Lenz Brendan M
• Berczik Douglas M

Classifications

• Y02T50/60

  Efficient propulsion technologies, e.g. for aircraft · CPC title

• C25D7/008

  Thermal barrier coatings · CPC title

• C25D3/54

  of metals not provided for in groups C25D3/04 - C25D3/50 · CPC title

• F05D2300/15

  Rare earth metals, i.e. Sc, Y, lanthanides · CPC title

• C25D3/46

  of silver · CPC title