Touch-up of layer paint oxides for gas turbine disks and seals
US7546683B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Dec 29, 2003 |
| Grant date | Jun 16, 2009 |
| Priority date | — |
| Expiry date | Dec 28, 2024 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY10T29/49885
- WIPO fieldBasic materials chemistry
- WIPO sectorChemistry
Abstract
The present invention is a process for applying oxide paint as a touch-up paint for an oxide-based corrosion inhibiting coating with at least one imperfection region. Such oxide-based corrosion inhibiting coatings are applied on superalloy components used for moderately high temperature applications, such as the superalloy components found in the high-pressure turbine (HPT) section of a gas turbine engine, including turbine disks and seals. However, during the application of oxide-based corrosion inhibiting coatings, imperfection regions sometimes occur, exposing the superalloy substrate beneath the oxide-based corrosion inhibiting coating. Such imperfection regions can include a spalled region, a scratched region, a chipped region, an uncoated region, or combinations thereof. The process of the present invention is useful where aircraft engine components have been treated with a corrosion inhibiting three-layer paint oxide system comprising chromia and alumina, but where a small imperfection region or regions within the layer oxide system are present after initial manufacture, refurbishment, or repair of the component.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.