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System and method for rejuvenating coated components of gas turbine engines

A technology for gas turbines and engines, applied in engine components, liquid fuel engines, components of pumping devices for elastic fluids, etc., can solve the problems of time-consuming and expensive turbine blades

Inactive Publication Date: 2017-08-29
GENERAL ELECTRIC CO
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Therefore, complete repair of turbine blades can be time-consuming and expensive

Method used

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  • System and method for rejuvenating coated components of gas turbine engines
  • System and method for rejuvenating coated components of gas turbine engines
  • System and method for rejuvenating coated components of gas turbine engines

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Embodiment Construction

[0164] Reference will now be made in detail to embodiments of the invention, one or more examples of which are illustrated in the accompanying drawings. Each example is provided by way of explanation of the invention, not limitation of the invention. In fact, it will be apparent to those skilled in the art that various modifications and variations can be made in the present invention without departing from the spirit or scope of the inventions. For example, features illustrated or described as part of one embodiment can be used with another embodiment to yield a still further embodiment. Thus, it is intended that the present invention covers such changes and modifications as come within the scope of the appended claims and their equivalents.

[0165] In this disclosure, chemical elements are discussed using their common chemical abbreviations, such as are commonly found on the Periodic Table of the Elements. For example, aluminum is represented by its common chemical abbrevi...

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Abstract

The present disclosure is directed to a method for rejuvenating a damaged coated component of a gas turbine engine (10). The method includes uninstalling the damaged coated component from the gas turbine engine (10). The method also includes isolating a first coated portion (105) of the component of the gas turbine engine (10) from a second coated portion (108) of the component. In addition, the method includes simultaneously depositing a first coating material (112) on the first coated portion (105) of the component and a different, second coating material (114) on the second coated portion (108) of the component. The method also includes reinstalling the rejuvenated coated component into the gas turbine engine (10).

Description

technical field [0001] The present invention relates generally to gas turbine engines and, more particularly, to systems and methods for the restoration of coated components, such as turbine blades, by simultaneous deposition of multiple coatings. Background technique [0002] A gas turbine engine generally includes a compressor section, a combustion section, a turbine section, and an exhaust section in series flow order. In operation, air enters the inlet of the compressor section where one or more axial or centrifugal compressors gradually compress the air until it reaches the combustion section. Fuel is mixed with compressed air and incinerated in the combustion section to provide combustion gases. Combustion gases are routed from the combustion section through a hot gas path defined within the turbine section and then exhausted from the turbine section via the exhaust section. [0003] In a particular configuration, the turbine section includes a high pressure (HP) tur...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B23P6/00B05D1/00B05D1/32
CPCB05D1/00B05D1/32B23P6/002F01D5/005F01D5/288F05D2220/32F05D2230/80F05D2230/90F05D2300/121F05D2300/132C23C10/04C23C18/1619C23C18/1633C23C30/00F01D9/02F01D25/24F04D29/324F04D29/388F04D29/522F04D29/542F04D29/545F05D2230/60F05D2230/70F05D2300/1431F05D2300/222
Inventor B.K.古普塔M.罗森斯韦格
Owner GENERAL ELECTRIC CO