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Coating and coating method for gas turbine engine component

a gas turbine engine and coating technology, applied in the direction of liquid fuel engine components, solid-state diffusion coatings, electrodialysis, etc., can solve the problems of ineffective masking in these processes and inability to apply in high-temperature processes

Inactive Publication Date: 2016-01-14
HOWMET CORPORATION
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Benefits of technology

The present invention provides a method for coating gas turbine components with a duplex coating that includes an aluminum-bearing coating and a chromium-bearing coating. This allows for different regions of the gas turbine component to be protected against temperature and oxidation / corrosion environments. The method involves applying a mask to the root region of the component, then applying the aluminum-bearing coating to the airfoil region and diffusing chromium into the alloy to form a chromium-enriched diffused surface coating on the root region. This method improves the durability and functionality of gas turbine components.

Problems solved by technology

Since pack and vapor phase chromizing require high temperature application above 1900 F and are difficult to apply to localized part areas of interest, these processes must be applied early in the part routing to the entire the part.
Masking has not been effective in these processes as a means for controlling the localized deposition of the chromium on certain areas of interest and, as a result, has not been applied in these high temperature processes.

Method used

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  • Coating and coating method for gas turbine engine component
  • Coating and coating method for gas turbine engine component
  • Coating and coating method for gas turbine engine component

Examples

Experimental program
Comparison scheme
Effect test

example 1

[0043]Pursuant to an illustrative embodiment of the present invention, the following processing steps are employed:

[0044]1. If a platinum-modified diffusion aluminide coating is to be formed on the gas path surfaces 12, 20a, then these surfaces are optionally electroplated with a layer of Pt pursuant to U.S. Pat. No. 5,788,832 which is already incorporated herein by reference. If a simple diffusion aluminde coating is to be formed, then this step is omitted.

[0045]2. Masking the second region of the turbine blade (i.e. root region 14 and platform surface 20b) with the M1 maskant powder mentioned above in a containment box. That is, the root region 14 and platform surface 20b are embedded in the maskant powder in the containment box.

[0046]3. Aluminize the first hotter region (i.e. airfoil 12 and platform surface 20a) to form a diffusion aluminide coating, such as a Pt-modified diffusion aluminide coating if step 1 is practiced, with the masking covering the second region.

[0047]4. Mask...

example 2

[0070]Pursuant to another illustrative embodiment of the present invention, the following processing steps are employed:

[0071]1. If a platinum-modified diffusion aluminide coating is to be formed on the gas path surfaces 12, 20a, then these surfaces are optionally electroplated with a layer of Pt pursuant to U.S. Pat. No. 5,788,832 which is already incorporated herein by reference. If a simple diffusion aluminide coating is to be formed, then this step is omitted.

[0072]2. Aluminize the first hotter region and the second region to form a diffusion aluminide coating, such as a Pt-modified diffusion aluminide coating. No masking covering the second region.

[0073]3. Removing the diffusion aluminide coating selectively from the second region by grit blasting, machining or other technique to expose the substrate alloy, while leaving the diffusion aluminide coating on the first region.

[0074]4. Masking the diffusion aluminide coating on the first region as described in Example 1.

[0075]5. Cr ...

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Abstract

The present invention provides a protective coating for a gas turbine blade or other component wherein the duplex coating includes an aluminum-bearing coating, such as a diffusion aluminide, formed on a first, relatively higher temperature region of the blade / component and a later-applied chromium-bearing diffusion coating formed on an adjacent relatively lower temperature region of the blade / component subject to hot corrosion in service. The chromium-bearing coating is applied after the aluminum-bearing coating by masking that coating and depositing a metallic chromium coating on the adjacent region followed by diffusing the chromium into the blade / component alloy to form a chromium-enriched diffusion coating thereon.

Description

RELATED APPLICATION[0001]This application claims benefit and priority of U.S. provisional application Ser. No. 61 / 633,935 filed Feb. 21, 2012, the entire disclosure of which is incorporated herein by reference.FIELD OF THE INVENTION[0002]The present invention relates to a protective coating for a gas turbine blade or other component wherein the coating includes an aluminum-bearing coating applied at a relatively high temperature region of the component and a chromium-bearing coating applied at another relatively lower temperature region of the component depending on coating functionality needed.BACKGROUND OF THE INVENTION[0003]Current gas turbine designs are requiring that a variety of coatings be applied to different areas of the turbine part for different functional reasons. Examples of coating functionality include wear, oxidation, thermal barrier, and hot corrosion. Turbine designers choose an appropriate coating for a particular functionality in the gas turbine environment.[000...

Claims

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Application Information

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Patent Type & Authority Applications(United States)
IPC IPC(8): F01D5/28C25D5/02C25D5/12C25D13/02C25D13/16
CPCF01D5/288C25D5/022C25D13/16C25D13/02C25D5/12C23C10/02C23C10/58C25D13/12F01D5/3007F05D2300/132F05D2300/121C25D5/44C25D5/50F05D2230/31C25D3/04
Inventor MURPHY, KENNETH S.BASTA, WILLIAM C.
Owner HOWMET CORPORATION
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