Molybdenum-silicon-boron with noble metal barrier layer

Patent metadata

Field	Value
Publication number	US-2017321558-A1
Application number	US-201615149344-A
Country	US
Kind code	A1
Filing date	May 9, 2016
Priority date	May 9, 2016
Publication date	Nov 9, 2017
Grant date	—

Abstract

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.

First claim

What is claimed is:

1 . An article comprising:
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.

2 . The article as recited in claim 1 , further comprising a metal interlayer disposed between the substrate and the barrier layer.

3 . The article as recited in claim 2 , 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.

4 . The article as recited in claim 2 , wherein the metal interlayer includes copper.

5 . 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.

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

7 . The article as recited in claim 1 , further comprising a topcoat disposed on the barrier layer.

8 . The article as recited in claim 7 , wherein the topcoat is formed of a silica material.

9 . 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.

10 . 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.

11 . The method as recited in claim 10 , further comprising, prior to depositing the barrier layer, depositing a metal interlayer onto the substrate.

12 . The method as recited in claim 11 , 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.

13 . The method as recited in claim 12 , 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.

14 . The method as recited in claim 11 , including depositing the metal interlayer and depositing the barrier layer using electroplating.

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

16 . A gas turbine engine 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, 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.

17 . The gas turbine engine as recited in claim 16 , further comprising a metal interlayer disposed between the substrate and the barrier layer.

18 . The gas turbine engine as recited in claim 17 , 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.

19 . The gas turbine engine as recited in claim 16 , 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.

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

Assignees

• United Technologies Corp

Inventors

• Lenz Brendan M
• Berczik Douglas M

Classifications

• F02C3/04

  having a turbine driving a compressor (power transmission arrangements F02C7/36; control of working fluid flow F02C9/16) · CPC title

• C25D3/50

  of platinum group metals · CPC title

• F05D2300/15

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

• C25D5/50

  by heat-treatment · CPC title

• C25D3/48

  of gold · CPC title