Gas turbine engine component with protective coating

Patent metadata

Field	Value
Publication number	US-10934860-B2
Application number	US-201715602436-A
Country	US
Kind code	B2
Filing date	May 23, 2017
Priority date	Jun 21, 2016
Publication date	Mar 2, 2021
Grant date	Mar 2, 2021

Abstract

A gas turbine engine component made of a nickel-based superalloy, the gas turbine engine component comprising a protective coating. The protective coating includes an inner diffusion barrier layer including any one or any combination of elements selected from the group consisting of platinum, palladium, tantalum, tungsten, hafnium and iridium, and an outer layer of hard material formed of hard particles embedded in a matrix.

First claim

The invention claimed is:

1. A gas turbine engine component made of a nickel-based superalloy, the gas turbine engine component comprising a protective coating including:
a diffusion barrier layer including any one or any combination of elements selected from the group consisting of platinum, palladium, tantalum, tungsten, hafnium and iridium,
an outer layer of hard material formed of hard particles embedded in a matrix, and
an entrapment layer of nickel immediately beneath the outer layer; wherein
the diffusion barrier layer prevents diffusion bonding of the protective coating to the gas turbine engine component;
the diffusion barrier layer of the protective coating is formed directly on the gas turbine engine component, the diffusion barrier layer and the outer layer being applied to the gas turbine engine component by successive procedures, the successive procedures being selected from the group consisting of electroplating, thermal spraying, plasma vapour deposition, chemical vapour deposition and sputtering, and
the matrix of the outer layer has a thickness which is less than the longest dimension of the hard particles so that one or more of the hard particles extend from the nickel entrapment layer through the matrix so as to protrude from the surface of the outer layer.

2. A component according to claim 1 , wherein the selected element(s) of the diffusion barrier layer form at least 80% by weight of the mass of the diffusion barrier layer.

3. A component according to claim 1 , wherein the hard particles are cubic boron nitride.

4. A component according to claim 1 , wherein the matrix is Co—CrC, Ni or Ni alloy.

5. A component according to claim 1 , wherein the outer layer and the diffusion barrier layer are applied by successive electroplating procedures.

6. A component according to claim 1 , wherein
the protective coating further includes a separation layer of nickel between the diffusion barrier layer and the outer layer, the separation layer spacing the hard particles from the diffusion barrier layer, and
the separation layer is applied on the diffusion barrier layer, before the application of the outer layer, by a procedure selected from the group consisting of electroplating, thermal spraying, plasma vapour deposition, chemical vapour deposition and sputtering.

7. A component according to claim 1 , wherein
a side of the hard particles of the outer layer being entrapped in the entrapment layer to hold the hard particles in position before encapsulation of the hard particles in the matrix of the outer layer, and
the entrapment layer is applied, before the application of the outer layer, by a procedure selected from the group consisting of electroplating, thermal spraying, plasma vapour deposition, chemical vapour deposition and sputtering.

8. A component according to claim 1 , wherein the component has one or more seal fins having the protective coating.

9. A component according to claim 1 , wherein the component is a rotor blade, a rotor disc or rotor drum.

10. A component according to claim 1 , wherein the diffusion barrier layer does not comprise the element nickel.

11. A component according to claim 1 , wherein the diffusion barrier layer consists of any one or any combination of elements selected from the group consisting of platinum, palladium, tantalum, tungsten, hafnium and iridium.

12. A component according to claim 1 , wherein the diffusion barrier layer comprises two or more layers.

13. A gas turbine engine having a component according to claim 1 .

14. A method comprising: introducing the component according to claim 1 to a gas turbine engine, wherein the component is exposed to temperatures above 600° C. during use of the component.

15. A gas turbine engine component made of a nickel-based superalloy, the gas turbine engine component comprising a protective coating including:
a diffusion barrier layer excluding nickel, but including any one or any combination of elements selected from the group consisting of platinum, palladium, tantalum, tungsten, hafnium and iridium,
an outer layer of hard material formed of hard particles embedded in a matrix, and
an entrapment layer of nickel immediately beneath the outer layer; wherein
the diffusion barrier layer prevents diffusion bonding of the protective coating to the gas turbine engine component,
the diffusion barrier layer and the outer layer are applied by successive procedures, the successive procedures being selected from the group consisting of electroplating, thermal spraying, plasma vapour deposition, chemical vapour deposition and sputtering, and
the matrix of the outer layer has a thickness which is less than the longest dimension of the hard particles so that one or more of the hard particles extend from the nickel entrapment layer through the matrix so as to protrude from the surface of the outer layer.

16. A gas turbine engine component made of a nickel-based superalloy, the gas turbine engine component comprising a protective coating including:
a diffusion barrier layer consisting of any one or any combination of elements selected from the group consisting of platinum, palladium, tantalum, tungsten, hafnium and iridium,
an outer layer of hard material formed of hard particles embedded in a matrix, and
an entrapment layer of nickel immediately beneath the outer layer; wherein
the diffusion barrier layer prevents diffusion bonding of the protective coating to the gas turbine engine component,
the diffusion barrier layer and the outer layer are applied by successive procedures, the successive procedures being selected from the group consisting of electroplating, thermal spraying, plasma vapour deposition, chemical vapour deposition and sputtering, and
the matrix of the outer layer has a thickness which is less than the longest dimension of the hard particles so that one or more of the hard particles extend from the nickel entrapment layer through the matrix so as to protrude from the surface of the outer layer.

17. A component according to claim 1 , wherein at least about 50%, by number, of the hard particles extend from the nickel entrapment layer through the matrix so as to protrude from the surface of the outer layer.

18. A component according to claim 1 , wherein at least about 80%, by number, of the hard particles extend from the nickel entrapment layer through the matrix so as to protrude from the surface of the outer layer.

19. A component according to claim 1 , wherein at least about 95%, by number, of the hard particles extend from the nickel entrapment layer through the matrix so as to protrude from the surface of the outer layer.

Assignees

• Rolls Royce Plc

Inventors

• Gibson Grant J
• Hancock Matthew
• Pallett Lloyd

Classifications

• F01D11/122

  with erodable or abradable material (blades having cutting or grinding tips F01D5/20) · CPC title

• C25D5/14

  two or more layers being of nickel or chromium, e.g. duplex or triplex layers · CPC title

• C25D7/008

  Thermal barrier coatings · CPC title

• F05D2300/6032

  Metal matrix composites [MMC] · CPC title

• F05D2230/30

  with deposition of material · CPC title