Abrasive coating for high temperature mechanical systems

Patent metadata

Field	Value
Publication number	US-10954803-B2
Application number	US-201916250752-A
Country	US
Kind code	B2
Filing date	Jan 17, 2019
Priority date	Jan 17, 2019
Publication date	Mar 23, 2021
Grant date	Mar 23, 2021

Abstract

In some examples, a method for forming an abrasive coating on a component (e.g., a turbine blade, vane, or knife ring) of a gas turbine engine. The method may include forming an abrasive coating system on a substrate, the abrasive coating system including an abrasive coating including a plurality of abrasive particles in a metal matrix; machining the abrasive coating on the substrate to define a machined abrasive coating having an abrasive coating thickness profile; and etching an outer surface of the machined abrasive coating to remove a portion of the metal matrix and form an etched metal matrix such that the abrasive particles protrude from the metal matrix.

First claim

The invention claimed is:

1. A method comprising:
depositing a plurality of abrasive particles and a metal matrix material on a substrate;
melting the metal matrix material via a directed energy source, wherein, upon solidification, the molten metal matrix material forms a metal matrix that attaches the plurality of abrasive particles to the substrate, wherein the metal matrix and the plurality of abrasive particles define an abrasive coating on the substrate;
machining the abrasive coating on the substrate to define a machined abrasive coating having an abrasive coating thickness profile; and
etching an outer surface of the machined abrasive coating to remove a portion of the metal matrix and form an etched metal matrix such that the abrasive particles protrude from the metal matrix.

2. The method of claim 1 , wherein the abrasive particles protrude about 1 micron to about 760 microns from the etched metal matrix.

3. The method of claim 1 , wherein the etched metal matrix defines a thickness of about 20 microns to about 760 microns.

4. The method of claim 1 , wherein the abrasive coating defines a thickness of about 44 microns to about 1000 microns prior to machining.

5. The method of claim 1 , wherein the abrasive particles comprise at least one of cubic boron nitride particles, metal carbide particles, metal nitride particles, or metal oxide particles.

6. The method of claim 1 , wherein the metal matrix comprises at least one of nickel, titanium, magnesium, cobalt, aluminum, chromium, or alloys thereof.

7. The method of claim 1 , wherein etching the outer surface of the machined abrasive coating comprises at least one of electrolytically etching the outer surface of the machine abrasive coating or etching via immersion of the outer surface of the coating into an acid.

8. The method of claim 1 , wherein the substrate comprises a blade of a gas turbine engine, wherein the abrasive coating is formed on a blade tip of the blade, and wherein the abrasive coating system of the blade tip is configured to abrade an abradable layer of a blade track during operation of the gas turbine engine.

9. The method of claim 8 , wherein the abrasive coating thickness profile of the machine abrasive coating is defined such that a substantially continuous seal is formed between the blade and blade track during the operation after the abrasive coating has abraded the abradable layer of the blade track during the operation.

10. The method of claim 1 , wherein the substrate comprises superalloy substrate.

11. The method of claim 1 , wherein the abrasive coating comprises a plurality of abrasive layers formed sequentially on the substrate, and wherein each abrasive layer comprises the plurality of abrasive particles in the metal matrix.

12. The method of claim 1 , wherein melting the metal matrix material via the directed energy source comprises melting the metal matrix material via a laser.

13. The method of claim 1 , wherein, prior to machining the abrasive coating, the abrasive coating defines a thickness on the substrate that is greater than a thickness defined by the plurality of abrasive particles on the substrate.

14. The method of claim 1 , wherein depositing the plurality of abrasive particles and the metal matrix material on the substrate comprises depositing a powder including the plurality of abrasive particles and the metal matrix material on the substrate.

15. The method of claim 1 , wherein depositing the plurality of abrasive particles and the metal matrix material on the substrate comprises depositing a wire including the plurality of abrasive particles and the metal matrix material on the substrate.

16. A method comprising:
sequentially forming a plurality of abrasive layers on a substrate to form an abrasive coating on the substrate including the plurality of abrasive layers, wherein each respective abrasive layer of the plurality of abrasive layers is formed by at least:
depositing a plurality of abrasive particles and a metal matrix material on the substrate,
melting the metal matrix material via a directed energy source, wherein, upon solidification, the molten metal matrix material forms a metal matrix that attaches the plurality of abrasive particles to the substrate, wherein the metal matrix and the plurality of abrasive particles define the respective abrasive layer on the substrate;

machining the abrasive coating on the substrate to define a machined abrasive coating having an abrasive coating thickness profile; and
etching an outer surface of the machined abrasive coating to remove a portion of the metal matrix and form an etched metal matrix such that the abrasive particles protrude from the metal matrix.

17. The method of claim 16 , wherein melting the metal matrix material via the directed energy source comprises melting the metal matrix material via a laser.

18. The method of claim 16 , wherein depositing the plurality of abrasive particles and the metal matrix material on the substrate comprises depositing a powder including the plurality of abrasive particles and the metal matrix material on the substrate.

19. The method of claim 16 , wherein depositing the plurality of abrasive particles and the metal matrix material on the substrate comprises depositing a wire including the plurality of abrasive particles and the metal matrix material on the substrate.

20. The method of claim 16 , wherein the abrasive particles comprise at least one of cubic boron nitride particles, metal carbide particles, metal nitride particles, or metal oxide particles, wherein the metal matrix comprises at least one of nickel, titanium, magnesium, cobalt, aluminum, chromium, or alloys thereof, and wherein the substrate comprises superalloy substrate.

Assignees

• Rolls Royce Corp

Inventors

• Shuck Quinlan Yee

Classifications

• F05D2300/6033

  Ceramic matrix composites [CMC] · CPC title

• C22C19/05

  with chromium · CPC title

• F05D2300/226

  Carbides · CPC title

• F01D11/001

  for sealing space between stator blade and rotor · CPC title

• F05D2300/21

  Oxide ceramics · CPC title