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Recoating process and recoated turbine blade

a technology of coating process and turbine blade, which is applied in the direction of machines/engines, mechanical equipment, transportation and packaging, etc., can solve the problems of reducing overall operational efficiency, other undesirable features, and high cost of replacement of turbine blades

Inactive Publication Date: 2014-07-10
GENERAL ELECTRIC CO
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Benefits of technology

This patent describes a process for recoating turbine blades with a thermal barrier coating system. The process involves removing a portion of the thermal barrier coating system to form a stripped region, and then applying a bond recoat and a thermal barrier recoat in a step-wise manner to form a recoated turbine blade. This recoating process provides better protection and durability of the thermal barrier coating system on the turbine blade substrate. The technical effects of this process include improved high-temperature performance, reduced maintenance costs, and increased longevity of turbine blades.

Problems solved by technology

Extremely high temperatures and long cycle times result in properties that can benefit from repair or replacement.
For example, extremely high temperatures and exposure to certain materials, such as fuel, can result in oxidation, can result in fatigue, can result in damage, or other undesirable features.
Replacement of turbine blades can be expensive.
Removal of the turbine blades for replacement from service can result in operational downtime that can reduce overall operational efficiency.
Similarly, full stripping of coatings on turbine blades can be expensive due to time and materials expended in the stripping process and the recoating process.
Also, using more than one thermal barrier coating on a turbine blade can be undesirable aesthetically.
Individuals may improperly perceive that such differences relate to the quality or other properties of the turbine blade.
Such improper perceptions can result in decreased use and / or sales of such turbine blades.

Method used

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  • Recoating process and recoated turbine blade
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  • Recoating process and recoated turbine blade

Examples

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Embodiment Construction

[0020]Provided is an exemplary recoating process and recoated turbine blade. Embodiments of the present disclosure, for example, in comparison to processes and coated articles without partial stripping and partial recoating, permit operational downtime to be reduced, permit selective repair and replacement of turbine blades, permit conserved use of materials in recoating turbine blades, permit materials to be inspected after removal of a thermal barrier coating and / or bond coat prior to recoating (for example, permitting inspection of a base material), permit damage from complete stripping to be reduced or eliminated, or a combination thereof.

[0021]FIG. 1 schematically shows a recoating process 100. The recoating process 100 includes providing a coated turbine blade 201 (step 102), as is further described in the embodiments shown in FIGS. 2-5, removing a portion of a thermal barrier coating system 203 (step 104), as is further described in the embodiments shown in FIGS. 2-5, applyin...

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Abstract

Recoating process and recoated turbine blade are disclosed. The recoating process includes providing a coated turbine blade, then removing a portion of the thermal barrier coating system to form a partially-stripped turbine blade, then applying a bond recoat to the stripped region of the partially-stripped turbine blade; and then applying a thermal barrier recoat to the bond recoat to form a recoated turbine blade. The recoated turbine blade comprises the bond coating portion abutting the bond recoat, the thermal barrier coating portion abutting the thermal barrier recoat, and the stepped configuration. The coated turbine blade has a thermal barrier coating system positioned on a substrate. The partially-stripped turbine blade has a stripped region, a bond coating portion, a thermal barrier coating portion, and a stepped configuration.

Description

FIELD OF THE INVENTION [0001]The present invention is directed to manufacturing processes and manufactured components. More particularly, the present invention is directed to recoating turbine blades and recoated turbine blades.BACKGROUND OF THE INVENTION [0002]Gas turbine blades are affected by operational use. Extremely high temperatures and long cycle times result in properties that can benefit from repair or replacement. For example, extremely high temperatures and exposure to certain materials, such as fuel, can result in oxidation, can result in fatigue, can result in damage, or other undesirable features. To reduce or eliminate such effects, turbine blades are replaced or repaired at periodic intervals.[0003]Replacement of turbine blades can be expensive. Removal of the turbine blades for replacement from service can result in operational downtime that can reduce overall operational efficiency. As such, any reduction of such downtime can result in substantial improvements in ...

Claims

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Application Information

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IPC IPC(8): F01D5/28
CPCF01D5/288F01D5/005F05D2230/31Y10T428/12618
Inventor THOMPSON, CHRISTOPHER EDWARDWARD, JR., JOHN D.HUNT, MARK LAWRENCELOMAS, JONATHAN MATTHEWLEWIS, GARETH WILLIAM DAVIDDEPALMA, III, MICHAEL ANTHONY
Owner GENERAL ELECTRIC CO
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