Method for applying a NiA1 based coating by an electroplating technique

a technology of nia1 and electroplating technique, which is applied in the direction of solid-state diffusion coating, machines/engines, climate sustainability, etc., can solve the problems of not being able to produce a substantially phase layer by electrodeposition technique, and the advantages of nial alloy composition produced by electrodeposition have not been appreciated, etc., to achieve the effect of convenient adaptation, cost saving and optimal composition

Inactive Publication Date: 2010-01-28
GENERAL ELECTRIC CO
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Benefits of technology

[0022]One advantage of the present invention is the ability to specifically achieve the substantially β phase of NiAl alloy composition, with its related advantages, utilizing an electroplating technique. While existing art has taught the use of an NiAl electroplating bath, heretofore, the advantages of the β phase of NiAl alloy composition produced by electrodeposition have not been appreciated and no attempt has been made to produce a substantially β phase layer by electrodeposition techniques.
[0023]Another advantage of the present invention is that the metallic coating produced by this invention is a non-line of sight process, and therefore, can be utilized to coat complex shapes and articles having recessed surfaces and exposed surfaces of apertures.
[0024]Still another advantage is that much of the processing occurs at or near ambient temperature. This allows for cost savings during the manufacturing process over, for example, thermal spray techniques.
[0025]Still another advantage of the present invention is that post-aluminiding increases the Al-content of external surfaces and allows internal cooling passages to be coated, to provide the preferred β phase NiAl alloy composition of optimal composition.
[0026]Yet another advantage of the present invention is that the process can be easily adapted for use in airfoil material repair operations. It is advantageous to have the ability to repair a damaged section of an airfoil, rather than having to strip the entire TBC coating and completely re-bond and re-coat a TBC coating to the entire part.
[0027]Another advantage of the present invention is that the process can be easily retrofitted to existing VPA and CVD production processes. Continuing and often interrelated improvements in processes and materials, such as the improvements of the present invention, can provide cost reductions and major increases in the performance of devices such as aircraft gas turbine engines.

Problems solved by technology

While existing art has taught the use of an NiAl electroplating bath, heretofore, the advantages of the β phase of NiAl alloy composition produced by electrodeposition have not been appreciated and no attempt has been made to produce a substantially β phase layer by electrodeposition techniques.

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  • Method for applying a NiA1 based coating by an electroplating technique
  • Method for applying a NiA1 based coating by an electroplating technique

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Embodiment Construction

[0030]The present invention is generally applicable to components that operate within environments characterized by relatively high temperatures, and are therefore subject to severe thermal stresses and thermal cycling. Examples of such components include the high and low-pressure turbine nozzle blades and vanes, shrouds, combustor liners and augmentor hardware of gas turbine engines. The invention is particularly useful for articles of complex shape such as turbine blades and vanes.

[0031]Substrate materials often used in these aircraft engine articles and power generation equipment articles may include nickel, cobalt, or iron based superalloys. The alloys may be cast or wrought superalloys having high temperature capability. Examples of such substrate materials include GTD-111, GTD-222, René 80, René 41, René 125, Reneé 77, René N4, René N5, René N6, 4th generation single crystal superalloy MX-4, Hastelloy X, and cobalt-based HS-188.

[0032]According to a preferred embodiment, a comp...

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Abstract

The present invention provides a coated article made using a plating process, either electroless or electrolytic, whereby nickel is plated on the article using a solution that includes a suspension of powders or containing one or more of the following elements: Ni, Cr, Al, Zr, Hf, Ti, Ta, Si, Ca, Fe, Y and Ga. Optionally, the coating is then heat treated at a temperature above about 1600.degree. F. for an effective amount of time to allow to homogenize the coating by allowing effective interdiffusion between the species. The level of aluminum may be altered to produce a coating of the predominantly beta phase of the NiAl alloy composition. Optionally, a TBC layer is applied over the predominantly beta phase NiAl alloy composition metallic bond coat.

Description

CROSS REFERENCE TO RELATED APPLICATIONS[0001]This application is a Divisional of application Ser. No. 10 / 143,662 filed May 10, 2002.FIELD OF THE INVENTION[0002]This invention relates generally to components of the hot section of gas turbine engines, and in particular, to a method for achieving a predominantly β phase NiAl alloy composite coating by an electroplating technique.BACKGROUND OF THE INVENTION[0003]In gas turbine engines, for example, aircraft engines, air is drawn into the front of the engine, compressed by a shaft-mounted rotary compressor, and mixed with fuel. The mixture is burned, and the hot exhaust gases are passed through a turbine mounted on a shaft. The flow of gas turns the turbine, which turns the shaft and drives the compressor. The hot exhaust gases flow from the back of the engine, providing thrust that propels the aircraft forward.[0004]During operation of gas turbine engines, the temperatures of combustion gases may exceed 3,000 degrees F., considerably hi...

Claims

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Application Information

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Patent Type & AuthorityApplications(United States)
IPC IPC(8): F01D9/02F01D5/18C23C10/02C23C10/52C23C18/32C23C26/00C23C28/02C25D15/02
CPCC23C10/02C23C10/52C23C18/32C23C26/00Y02T50/67C23C28/324C23C28/325C23C28/3455C25D15/02C23C28/321Y02T50/60
InventorGRYLLS, RICHARD JOHNGROSSMAN, THEODORE ROBERT
OwnerGENERAL ELECTRIC CO