Method for manufacturing an abrasive coating on a gas turbine component

Patent metadata

Field	Value
Publication number	US-9322100-B2
Application number	US-45126307-A
Country	US
Kind code	B2
Filing date	May 4, 2007
Priority date	May 4, 2007
Publication date	Apr 26, 2016
Grant date	Apr 26, 2016

Abstract

A method for manufacturing an abrasive coating on a gas turbine component, especially on a gas turbine rotor blade tip, comprising at least the following steps: a) providing a gas turbine component, especially a gas turbine rotor blade; b) providing a high temperature melting alloy powder; c) providing abrasive particles; d) providing a low temperature melting alloy powder; e) blending at least said high temperature melting alloy powder and said abrasive particles to provide a mixture; f) applying said low temperature melting alloy powder and said mixture to an area of said gas turbine component, especially to a tip of said turbine rotor blade; g) locally heating said area of said gas turbine component to a temperature above the melting point of said low temperature melting alloy powder but below the melting point of said high temperature melting alloy powder is provided.

First claim

What is claimed is:

1. A method for manufacturing an abrasive coating on gas turbine component, comprising at least the following steps:
a) providing a gas turbine component;
b) providing a high temperature melting alloy powder;
c) providing abrasive particles;
d) providing a low temperature melting alloy powder;
e) blending at least said high temperature melting alloy powder and said abrasive particles to provide a mixture;
f) applying said low temperature melting alloy powder and said mixture to a first area of said gas turbine component; and
g) locally heating said first area of said gas turbine component to a first temperature above the melting point of said low temperature melting alloy powder but below the melting point of said high temperature melting alloy powder, while maintaining a second area of the gas turbine component adjacent to the first area at a second temperature lower than the first temperature.

2. The method according to claim 1 wherein said high temperature melting alloy powder is a nickel based super-alloy powder.

3. The method according to claim 1 wherein said high temperature melting alloy powder is a cobalt based super-alloy powder.

4. The method according to claim 1 wherein said high temperature melting alloy powder is a MCrAlY powder.

5. The method according to claim 1 wherein said abrasive particles are cubic boron nitride particles.

6. The method according to claim 1 wherein said abrasive particles are silicon nitride particles.

7. The method according to claim 1 wherein said abrasive particles are silicon aluminium oxynitride particles.

8. The method according to claim 1 wherein said low temperature melting alloy powder is nickel based brazing alloy powder having a melting point below the melting point of said high temperature melting alloy powder and below the melting point of the constituents of the first area of said gas turbine component.

9. The method according to claim 1 wherein the locally heating is accomplished by induction heating.

10. The method according to claim 1 wherein said low temperature melting alloy powder is applied in a separate layer to the first area of said gas turbine component above a layer of said mixture of said high temperature melting alloy powder and said abrasive particles.

11. The method according to claim 1 wherein within step e) said low temperature melting alloy powder is blended together with said high temperature melting alloy powder and said abrasive particles to provide a mixture, and that the low temperature melting alloy powder, the high temperature melting alloy powder and the abrasive particles are applied in a single layer to the area of said gas turbine component.

12. The method according to claim 1 wherein the method is carried out in a vacuum or inert environment.

13. The method according to claim 1 wherein the gas turbine component is a gas turbine rotor blade and the first area is a tip of the gas turbine rotor blade.

14. The method as recited in claim 1 wherein the gas turbine component is a blade and the first area is a first section of the blade.

15. The method as recited in claim 14 wherein the first section is a blade tip.

16. The method as recited in claim 1 wherein the mixture is applied directly to the first area.

17. The method as recited in claim 1 wherein the mixture is applied to the first area before the low temperature melting alloy powder is applied to the area.

18. The method as recited in claim 1 wherein the low temperature melting alloy powder forms an outer layer over the mixture before the locally heating step.

19. A method for manufacturing an abrasive coating on gas turbine component, comprising at least the following steps:
a) providing a gas turbine component;
b) providing a high temperature melting alloy powder;
c) providing abrasive particles;
d) providing a low temperature melting alloy powder;
e) blending at least said high temperature melting alloy powder and said abrasive particles to provide a mixture;
f) applying said low temperature melting alloy powder and said mixture to an area of said gas turbine component, the high temperature melting alloy powder having a first melting point while on the area of the gas turbine component; and
g) locally heating said area of said gas turbine component to a temperature above the melting point of said low temperature melting alloy powder but below the melting point of said first melting point.

20. A method for manufacturing an abrasive coating on gas turbine component, comprising at least the following steps:
a) providing a gas turbine component;
b) providing a high temperature melting alloy powder;
c) providing abrasive particles;
d) providing a low temperature melting alloy powder;
e) blending at least said high temperature melting alloy powder and said abrasive particles to provide a mixture;
f1) applying said mixture to an area of said gas turbine component;
f2) applying said lower temperature meting alloy powder above the mixture; and
g) locally heating said area of said gas turbine component to a first temperature above the melting point of said low temperature melting alloy powder but below the melting point of said high temperature melting alloy powder.

Assignees

• Manier Karl-Heinz
• Chuprakov Ilya
• Sparling Robert
• Mtu Aero Engines Gmbh
• Liburdi Engineering

Inventors

• Manier Karl-Heinz
• Chuprakov Ilya
• Sparling Robert

Classifications

• F01D5/288

  Protective coatings for blades · CPC title

• F05D2300/2283

  of silicon · CPC title

• C23C30/00 Primary

  Coating with metallic material characterised only by the composition of the metallic material, i.e. not characterised by the coating process (C23C26/00, C23C28/00 take precedence) · CPC title

• F05D2230/30

  with deposition of material · CPC title

• C23C24/10 Primary

  with intermediate formation of a liquid phase in the layer · CPC title