Method for coating a component for the hot gas duct of a turbomachine

Patent metadata

Field	Value
Publication number	US-11359289-B2
Application number	US-201816033984-A
Country	US
Kind code	B2
Filing date	Jul 12, 2018
Priority date	Jul 14, 2017
Publication date	Jun 14, 2022
Grant date	Jun 14, 2022

Abstract

The invention relates to a method for coating a component, which is provided for the hot gas duct of a turbomachine, wherein the coating material is applied onto the uncoated component surface in the form of particles in mixture with a binding agent, and the component with the particle-treated binding agent thereupon then undergoes thermal treatment in such a way that the binding agent is released and the coating material remains on the component.

First claim

What is claimed is:

1. A method for coating a component with a coating material, which component is provided for arrangement in the hot gas duct in a turbine center frame of a turbomachine, as a hot gas duct panel or as a fairing of a support strut supporting the bearing of the turbine shaft, comprising the steps of:
keeping the coating material or a precursor thereof in the form of particles in mixture with a binding agent;
applying a coat of the particle-treated binding agent onto a region of the component the entirety of which is not precoated; and
thermally treating the component with the particle-treated binding agent on it so that the binding agent is released and the coating material remains on the component; and
wherein the second region is a functional surface-area region of the surface of the component that represents a mounting boundary in regard to an assembly of the component with other components in the turbomachine, which remains uncoated, and
wherein a surface-area proportion of at least 10% of a portion of the surface of the component exposed to the hot gas is coated and at least 20% of the surface exposed to the hot gas is uncoated; and
wherein the particle-treated binding agent is applied prior to the step of thermally treating sequentially in at least two non-coextensive coats, which have at least one partial overlap with one another on the surface of the component providing a progressive stepped coating.

2. The method according to claim 1 , wherein the particles comprise aluminum, which diffuses proportionately into the surface of the component during the thermal treatment and/or in which the coat is applied by spraying and/or by brushing, in particular locally.

3. The method according to claim 1 , wherein the component is made of a nickel alloy.

4. The method according to claim 1 , wherein the binding agent is provided on an organic base and undergoes pyrolysis during the thermal treatment.

5. The method according to claim 1 , wherein the step of thermally treating the component is carried out at least at 800° C. and at most at 1200° C.

6. The method according to claim 1 , wherein a surface-area proportion of at most 80% of a portion of the surface of the component exposed to the hot gas is coated.

7. The method according to claim 1 , wherein, in relation to a flow in the hot gas duct, the component has a leading edge and a trailing edge as well as, further, two lateral surfaces that join the leading edge and the trailing edge to each other, wherein the leading edge and/or the trailing edge are each coated at least over a major part of their respective extent, but the lateral surfaces each remain uncoated at least in some regions.

8. The method according to claim 1 , wherein the region of the surface on which the particle-treated binding agent is applied is masked with a mask during the application of the particle-treated binding agent.

9. The method according to claim 8 , further comprising the steps of:
providing a used component that was coated with the coating material;
revising and re-coating the used component, wherein, also during the re-coating, a particle-treated binding agent is applied using the same mask for the re-coating.

10. The method according to claim 1 , wherein the component is coated only in regions, by use of a local masking, and a region that is unmasked during the coating remains uncoated.

11. The method according to claim 10 , wherein a coated component is configured and arranged for use in a hot gas duct of a turbomachine.

Assignees

• MTU Aero Engines AG

Inventors

• Metscher Martin
• Heidenreich Benedikt
• Haegert Jan
• Hiller Nils
• Lang Patrick

Classifications

• C23C10/20

  only one element being diffused · CPC title

• F05D2230/31

  Layer deposition · CPC title

• F01D5/288

  Protective coatings for blades · CPC title

• F01D25/005

  Selecting particular materials · CPC title

• F05D2240/10

  Stators · CPC title