Process for producing a run-in coating

Patent metadata

Field	Value
Publication number	US-9845685-B2
Application number	US-201313856235-A
Country	US
Kind code	B2
Filing date	Apr 3, 2013
Priority date	Apr 4, 2012
Publication date	Dec 19, 2017
Grant date	Dec 19, 2017

Abstract

Disclosed is a process for producing a run-in coating ( 20, 24, 32, 44 ) on a component of a turbomachine, in particular of a gas turbine. The run-in coating is applied and produced on the component of the turbomachine by a kinetic cold gas compacting process (K3). The invention also encompasses a run-in coating for a static or rotating component of a turbomachine and a static or rotating component of a turbomachine, in particular of a gas turbine, having at least one run-in coating.

First claim

What is claimed is:

1. A process for producing a run-in coating on a static or rotating component of a turbomachine, wherein the run-in coating is applied and produced on the component by a kinetic cold gas compacting process (K3) and is applied to the component according to a predetermined layer pattern to form at least one of a structure and a contour at least one of on and in the run-in coating.

2. The process of claim 1 , wherein a honeycomb structure is formed as the at least one of a structure and a contour at least one of on and in the run-in coating.

3. The process of claim 1 , wherein prior to applying the run-in coating at least one of a bonding layer, a thermal barrier layer, or a titanium fire protection layer is applied to a surface of the component to be coated with the run-in coating to form a composite run-in coating.

4. The process of claim 3 , wherein the at least one of a bonding layer, thermal barrier layer, or titanium fire protection layer is produced by a thermal spraying process.

5. The process of claim 1 , wherein the run-in coating comprises an aluminum alloy.

6. A run-in coating for a static or rotating component of a turbomachine, wherein the coating is produced by the process of claim 1 .

7. A static or rotating component of a turbomachine, wherein the component is a rotor blade tip, an outer shroud of a rotor blade or of a row of rotor blades, or a housing of a compressor component or turbine component and comprises the run-in coating of claim 6 .

8. A process for producing a run-in coating on a static or rotating component of a turbomachine, wherein the run-in coating is applied and produced on the component by a kinetic cold gas compacting process (K3) and after application of the run-in coating to the component at least one of a structure and a contour is formed at least one of on and in the run-in coating by an electrochemical material removal process.

9. The process of claim 8 , wherein the electrochemical material removal process comprises at least one of electrochemical machining (ECM) and precise/pulsed electrochemical metal machining (PEM/PECM).

10. The process of claim 8 , wherein the run-in coating comprises an aluminum alloy.

11. A run-in coating for a static or rotating component of a turbomachine, wherein the coating is produced by the process of claim 8 .

12. A static or rotating component of a turbomachine, wherein the component is a rotor blade tip, an outer shroud of a rotor blade or of a row of rotor blades, or a housing of a compressor component or turbine component and comprises the run-in coating of claim 11 .

13. A process for producing a run-in coating on a static or rotating component of a turbomachine, wherein the run-in coating is applied and produced on the component by a kinetic cold gas compacting process (K3) and wherein after application of the run-in coating to the component a honeycomb structure is formed at least one of on and in the run-in coating.

14. The process of claim 13 , wherein the honeycomb structure is formed by an electrochemical material removal process.

15. The process of claim 14 , wherein the electrochemical material removal process comprises at least one of electrochemical machining (ECM) and precise/pulsed electrochemical metal machining (PEM/PECM).

16. The process of claim 13 , wherein the honeycomb structure is formed by a mechanical material removal process.

17. The process of claim 16 , wherein the mechanical material removal process comprises drilling.

18. The process of claim 13 , wherein the run-in coating comprises an aluminum alloy.

19. A run-in coating for a static or rotating component of a turbomachine, wherein the coating is produced by the process of claim 13 .

20. A static or rotating component of a turbomachine, wherein the component is a rotor blade tip, an outer shroud of a rotor blade or of a row of rotor blades, or a housing of a compressor component or turbine component and comprises the run-in coating of claim 19 .

Assignees

• Mtu Aero Engines Gmbh

Inventors

• Stiehler Frank
• Hertter Manuel

Classifications

• F01D5/147 Primary

  Construction, i.e. structural features, e.g. of weight-saving hollow blades (F01D5/148, F01D5/16 and F01D5/20 take precedence; blade shape F01D5/141; blades with cooling or heating channels or cavities F01D5/18; heating, heat-insulating or cooling means on blades F01D5/18) · CPC title

• F01D11/122

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

• F02C7/25

  Fire protection or prevention (in general A62) · CPC title

• F05D2240/307

  related to the tip of a rotor blade · CPC title

• F01D11/127

  with a deformable or crushable structure, e.g. honeycomb · CPC title