General Electric Company

Other

General Electric Aviation Service Operation Pte. Ltd.

Genfa Hu

Keng N Chen

Lawrence Bernard Kool

Nigel Brian Thomas Langley

Kwok Heng Yow

Shih Tung Ngiam

The present invention is directed to a method for recovery of platinum from a coating on a component, wherein the coating includes platinum aluminide, the method including: contacting the coating on the component with a reagent solution, the reagent solution including a reactive species capable of solubilizing an aluminum salt in water, which results in formation of a platinum-rich residue on the component; separating the platinum-rich residue from the component; and collecting the platinum-rich residue. The reactive species may be hexafluorosilicic acid.

Platinum recovery methods

A gas turbine blade which has previously been in service is protected by cleaning the gas turbine blade, and then first depositing a platinum first layer on the airfoil and the platform of the gas turbine blade. Thereafter, a platinum second layer is deposited over the platform but not the airfoil. A platinum-aluminide protective coating is formed by depositing an aluminum-containing layer overlying both the platform and the airfoil and interdiffusing the platinum and the aluminum.

Method for selective surface protection of a gas turbine blade which has previously been in service

An improved coating and method for applying the coating to minimize the consumption of substrate material during high temperature service by formation of an intermediate metal aluminide layer. A layer of Ni or Co or combinations of Ni and Co are added to the substrate material as an overlay by a process such as electroplating or electroless plating. A diffusion aluminide is then formed at the surface by exposing the plated substrate to a source of aluminum at an elevated temperature.

Coating and method for minimizing consumption of base material during high temperature service

A method for identifying and repairing indications open to the surface of a turbine component, such as cracks or other tight crevices that may develop during turbine engine operation. The process includes cleaning the component of debris, dirt or other foreign material that may otherwise mask the presence of the indications. This is followed by applying a fluorescent penetrant to the surface of the component. Without removing the penetrant, the article is visually inspected under normal lighting conditions and repair alloy is applied as needed to areas requiring repair. Next, the article is inspected under an ultraviolet light, at which time very tight indications not otherwise detectable by the unaided eye are identified as areas requiring repair and repair alloy is applied to these additional areas, by an automatic and/or manual process. Without removing the penetrant, the article is then heated to an elevated temperature sufficient to liquify at least a portion of the repair alloy to accomplish the repair.

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Singapore, Singapore

Genfa Hu