Gas turbine engine component with protective coating

Patent metadata

Field	Value
Publication number	US-2017362944-A1
Application number	US-201715602436-A
Country	US
Kind code	A1
Filing date	May 23, 2017
Priority date	Jun 21, 2016
Publication date	Dec 21, 2017
Grant date	—

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

1 . A gas turbine engine component made of a nickel-based superalloy, the gas turbine engine component comprising a protective coating including:
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.

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

6 . A component according to claim 1 , wherein the protective coating further includes a separation layer of nickel between the diffusion barrier and the outer layer, the separation layer spacing the hard particles from the diffusion barrier layer.

7 . A component according to claim 1 , wherein the protective coating further includes an entrapment layer of nickel immediately beneath the outer layer, undersides 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.

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 inner 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.

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

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

14 . Use of the component according to claim 1 in a gas turbine engine at temperatures above 600° C.

15 . A gas turbine engine component made of a nickel-based superalloy, the gas turbine engine component comprising a protective coating including:
an inner 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, and an outer layer of hard material formed of hard particles embedded in a matrix.

16 . A gas turbine engine component made of a nickel-based superalloy, the gas turbine engine component comprising a protective coating including:
an inner 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, and an outer layer of hard material formed of hard particles embedded in a matrix.

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

• C25D7/008

  Thermal barrier coatings · CPC title

• F05D2230/30

  with deposition of material · CPC title

• F01D5/02

  Blade-carrying members, e.g. rotors (rotors of non-bladed type F01D1/34; stators F01D9/00 {; selecting particular materials F01D5/28}) · CPC title

• F05D2220/32

  in gas turbines · CPC title