Treatment process, oxide-forming treatment composition, and treated component

Patent metadata

Field	Value
Publication number	US-9970305-B2
Application number	US-201514857912-A
Country	US
Kind code	B2
Filing date	Sep 18, 2015
Priority date	Sep 18, 2015
Publication date	May 15, 2018
Grant date	May 15, 2018

Abstract

A treatment process for a gas turbine component comprising a bond coating and a ceramic coating, an oxide-forming treatment composition, and a treated component are disclosed. The ceramic coating is contacted with a treatment composition. The treatment composition includes a carrier and a particulate oxide-forming material suspended within the carrier. The particulate oxide-forming material is one or more of yttria oxide, antimony, or tin oxide. The treatment composition is heated to form an oxide overlay coating on the ceramic coating. The treated component includes a ceramic coating and one or both of a corrosion inhibitor and an oxide formed by an oxide-forming treatment composition having the corrosion inhibitor.

First claim

What is claimed is:

1. A treatment process for a gas turbine component comprising a bond coating and a ceramic coating, the process comprising:
contacting the ceramic coating with a treatment composition, the treatment composition comprising a carrier; and a particulate oxide-forming material suspended within the carrier, the particulate oxide-forming material being selected from the group consisting of antimony, tin oxide, and combinations thereof;
heating the treatment composition to form an oxide overlay coating on the ceramic coating.

2. The treatment process of claim 1 , wherein the contacting includes applying the treatment composition by a technique selected from the group consisting of brushing, dipping, injecting, condensing, spraying, and combinations thereof.

3. The treatment process of claim 1 , wherein the heating of the treatment composition is to a temperature of between about 800° F. and about 1200° F.

4. The treatment process of claim 1 , wherein the oxide overlay coating formed penetrates into regions of the ceramic coating selected from the group consisting of cracks, pores, asperities, machined features, delaminations, and combinations thereof.

5. The treatment process of claim 1 , wherein the ceramic coating is within a hot-gas path of the gas turbine component.

6. The treatment process of claim 1 , further comprising operating the gas turbine then reapplying the treatment composition and heating the treatment composition.

7. The treatment process of claim 1 , further comprising operating the gas turbine with a crude oil fuel.

Assignees

• Gen Electric

Inventors

• Everhart Richard Todd

Classifications

• C23C8/42 Primary

  only one element being applied · CPC title

• F05D2230/90

  Coating; Surface treatment · CPC title

• F05D2240/35

  Combustors or associated equipment · CPC title

• F05D2300/611

  Coating · CPC title

• F23R3/42

  characterised by the arrangement or form of the flame tubes or combustion chambers · CPC title