Coated gas turbine engine components

Patent metadata

Field	Value
Publication number	US-10072506-B2
Application number	US-201514734834-A
Country	US
Kind code	B2
Filing date	Jun 9, 2015
Priority date	Jun 30, 2014
Publication date	Sep 11, 2018
Grant date	Sep 11, 2018

Abstract

A gas turbine engine component may include a coating adapted to protect the component during use. The coating may be applied by sintering metallic particles to form a metallic matrix fused to the component.

First claim

What is claimed is:

1. A method of making a coated gas turbine engine component, the method comprising:
depositing a layer of powder including metallic particles and abrasive particles on a gas turbine engine component; and
applying microwaves to the layer of powder to heat the metallic particles to a temperature below a melting temperature of the metallic particles to sinter the metallic particles into a metallic matrix joined to the gas turbine engine component.

2. The method of claim 1 , further comprising selecting the metallic particles from a group consisting of: nickel alloys, titanium alloys, cobalt alloys, refractory metal alloys and chrome alloys.

3. The method of claim 1 , further comprising selecting a particle size of the metallic particles such that the microwaves couple to the metallic particles.

4. The method of claim 1 , further comprising selecting a wavelength of the microwaves such that the microwaves couple to the metallic particles.

5. The method of claim 1 , further comprising selecting the abrasive particles from a group consisting of: cubic boron nitride, aluminum oxide, zirconium oxide, titanium carbide and silicon carbide.

6. The method of claim 1 , wherein a melting temperature of the abrasive particles is higher than the melting temperature of the metallic particles.

7. The method of claim 1 , further comprising applying a directed energy beam to the layer of powder to heat the metallic particles in order to fuse the metallic particles into the metallic matrix.

8. The method of claim 7 , wherein the applying the directed energy beam to the layer of powder is performed after the applying microwaves to the layer of powder or contemporaneously with at least a portion of the applying microwaves to the layer of powder.

9. The method of claim 1 , wherein the abrasive particles are less dense than the metallic matrix.

10. The method of claim 1 , wherein the abrasive particles comprise hollow spherical particles.

11. The method of claim 1 , further comprising selecting a wavelength of the microwaves such that the microwaves do not substantially couple to the abrasive particles.

Assignees

• Rolls Royce Corp

Inventors

• Shuck Quinlan Y

Classifications

• F01D5/20

  Specially-shaped blade tips to seal space between tips and stator {(F01D5/225 takes precedence)} · CPC title

• F01D11/001

  for sealing space between stator blade and rotor · CPC title

• F05D2230/22

  by sintering · CPC title

• F01D11/122

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

• F01D5/288 Primary

  Protective coatings for blades · CPC title