Touch-up of layer paint oxides for gas turbine disks and seals

Details Touch-up of layer paint oxides for gas turbine disks and seals Touch-up of layer paint oxides for gas turbine disks and seals

2003-12-29

2009-06-16

Bryant, David P (Department: 3726)

Metal working

Method of mechanical manufacture

Impeller making

C029S402180

Reexamination Certificate

active

07546683

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.

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