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Repair method for tbc coated turbine components

A component, turbine technology, applied in the field of repairing gas turbine engine components, which can solve the problems of high scrap rate, component wall loss, low labor cost productivity, etc.

Inactive Publication Date: 2010-06-16
GENERAL ELECTRIC CO
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Both processes have several disadvantages, including low labor cost productivity due to the manual nature of the process, process variance and rework, and part wall loss during chemical stripping, which results in high scrap rates

Method used

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  • Repair method for tbc coated turbine components
  • Repair method for tbc coated turbine components
  • Repair method for tbc coated turbine components

Examples

Experimental program
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Embodiment Construction

[0018] Referring to the drawings, wherein like reference numerals designate like elements throughout the several views, figure 1 An exemplary turbine nozzle segment 10 is shown. A gas turbine engine comprises a plurality of such sections 10 arranged in an annular array. The turbine nozzle segment 10 is only an example of a coated metal turbine component, and the repair methods described herein are equally applicable to other components, non-limiting examples of which include combustor liners, rotating turbine blades, and Turbine shroud.

[0019] The turbine nozzle 10 includes first and second nozzle vanes 12 disposed between an arcuate outer band 14 and an arcuate inner band 16 . The bucket 12 defines an airfoil configured to optimally direct the combustion gases to a turbine rotor (not shown) located downstream thereof. The outer and inner bands 14 and 16 define outer and inner radial boundaries, respectively, of the gas flow through the nozzle segment 10 . The interior o...

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Abstract

The present invention provides repair method for TBC coated turbine components, concretely provides a method for repairing a metallic turbine component which includes a thermal barrier coating system including a metallic bond coat (22) and a ceramic top coat (22). The method includes: (a) removing the top coat (24) using a mechanical process; (b) partially stripping the metallic bond coat (22) from the component, such that substantially no material of the component is removed; (c) repairing at least one defect in the turbine component; (d) applying a new metallic bond coat (26', 28') to the turbine component; and (e) applying a new ceramic top coat (24) over the metallic bond coat(26', 28').

Description

technical field [0001] The present invention relates generally to repairing gas turbine engine components, and more particularly to repairing turbine components including ceramic thermal barrier coatings. Background technique [0002] A gas turbine engine includes a "hot section" that includes a combustor and one or more downstream turbines. During operation the components in this hot section are exposed to high temperature, corrosive gas flows which limit their useful life. Consequently, these components are typically fabricated from high temperature cobalt- or nickel-based "superalloys" and are often coated with corrosion- and / or heat-resistant materials, particularly ceramic thermal barrier coatings (TBC) . [0003] Examples of such components include, but are not limited to, high pressure turbine blades and nozzles, and turbine blade shrouds. Despite the protective coating, such components often develop defects such as cracks, damage or loss of material during use. ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B23P6/00F01D5/28C23C30/00C22C19/05
CPCC23C28/3455F01D5/005F05B2230/90C23C28/00C23C4/04C23C28/321B23P6/007C23C28/3215F05D2230/90B23P6/045C23C4/02C23C28/325Y10T29/49318
Inventor B·K·古普塔W·R·格雷迪A·F·加西亚
Owner GENERAL ELECTRIC CO
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