Thermal barrier coating with reduced edge crack initiation stress and high insulating factor
US-2021348562-A1 · Nov 11, 2021 · US
Method for coating a component
US11873571B2 · US · B2
| Field | Value |
|---|---|
| Publication number | US-11873571-B2 |
| Application number | US-202217824088-A |
| Country | US |
| Kind code | B2 |
| Filing date | May 25, 2022 |
| Priority date | May 27, 2021 |
| Publication date | Jan 16, 2024 |
| Grant date | Jan 16, 2024 |
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- Title
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Abstract
Official abstract text for this publication.
The present invention is directed to a method for coating a component, wherein the component has a first and a second surface, and wherein the first and the second surface adjoin each other at an edge, in which method i) first of all, the edge between the first and the second surface is rounded, and ii) subsequently, a coating is applied to the first surface.
First claim
Opening claim text (preview).
What is claimed is: 1. A method for coating a blade body for a turbomachine, wherein the blade body has a first and a second surface and wherein the first and the second surface adjoin each other at an edge, the method comprising the steps of: i) first, rounding an entire length of the edge between the first and second surfaces, and ii) subsequently, applying a coating to the first surface, wherein the rounding of the edge in step i) comprises a processing with a brush prior to application of the coating to the first surface. 2. The method according to claim 1 , wherein a rounding introduced in step i) between the first and second surfaces has, as viewed in section, a radius of curvature R that corresponds to at least 0.5 times a thickness d of the coating, that is, R≥0.5·d. 3. The method according to claim 1 , wherein a rounding introduced in step i) between the first and second surfaces has, as viewed in a section, a radius of curvature R that corresponds to at most 5 times a thickness d of the coating, that is, R≤5·d. 4. The method according to claim 1 , wherein the first surface is processed in a material-removing manner prior to step i) and the edge is thereby produced. 5. The method according to claim 1 , wherein, in step i), after the processing with the brush and prior to application of the coating to the first surface, a grinding processing occurs. 6. The method according to claim 1 , wherein the coating is applied in a galvanic manner in step ii). 7. The method according to claim 1 , wherein the coating contains boron nitride. 8. The method according to claim 1 , wherein the first surface is a blade tip surface and the second surface is a side surface of the blade body. 9. A method for producing a blade body for a turbomachine, wherein the blade body is coated in a method in accordance with claim 1 .
Assignees
Inventors
Classifications
- C25D9/08Primary
by cathodic processes · CPC title
turbine or like blades from one piece · CPC title
Combined electrolytic and electrophoretic processes {with charged materials} · CPC title
by removing material · CPC title
Layer deposition · CPC title
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- What does patent US11873571B2 cover?
- The present invention is directed to a method for coating a component, wherein the component has a first and a second surface, and wherein the first and the second surface adjoin each other at an edge, in which method i) first of all, the edge between the first and the second surface is rounded, and ii) subsequently, a coating is applied to the first surface.
- Who is the assignee on this patent?
- MTU Aero Engines AG
- What technology area does this patent fall under?
- Primary CPC classification C25D9/08. Mapped technology areas include Chemistry & Metallurgy.
- When was this patent published?
- Publication date Tue Jan 16 2024 00:00:00 GMT+0000 (Coordinated Universal Time) (B2). Legal status and post-grant events are not shown on this page.
- What related patents are in patentsdb?
- We list 7 related publications on this page (citations in our corpus or others sharing the same primary CPC).