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Method of coating gas turbine components

A technology for turbines and parts, applied in sputtering coating, engine components, vacuum evaporation coating, etc., which can solve the problems of increased manufacturing time and increased costs

Inactive Publication Date: 2007-08-22
GENERAL ELECTRIC CO
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

These process steps can add cost and add approximately 7-10 days to manufacturing time

Method used

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  • Method of coating gas turbine components
  • Method of coating gas turbine components
  • Method of coating gas turbine components

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Embodiment Construction

[0015] A method of, for example, coating the inner and outer surfaces of a turbomachine part, such as a rotor blade, with an anti-oxidation coating while maintaining the properties of the nickel-aluminide coating will be described in detail below. The method includes coating the outer surface of a turbine part with a nilide coating and employing a vapor phase aluminization process to deposit a protective coating on the inner and outer surfaces of the turbine part to prevent oxidation and heat of the turbine part. corrosion. The process parameters are uniquely designed to provide an aluminide vapor composition in balance with the nickelalide outer surface when providing a coating to the inner surface.

[0016] Referring to the drawings, FIG. 1 is a schematic diagram of a gas turbine engine 10 including a blower assembly 12 and a core engine 13 including a high pressure compressor 14 , a combustor 16 and a high pressure turbine 18 . Engine 10 also includes a low pressure turbin...

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Abstract

A method of forming a metal coating on surfaces of internal passages of a turbine part (40) includes applying a nickel aluminum bond coating to an external surface of the turbine part, positioning the turbine part in a VPA chamber (88), coupling a gas manifold to at least one internal passage inlet, and coating at least a portion of the internal surface and the external of the turbine part by a vapor phase aluminiding (VPA) process using metal coating gases to form a coating on the internal surfaces of the turbine part.

Description

technical field [0001] The present invention relates generally to gas turbine engines, and more particularly to methods of depositing protective coatings on components of gas turbine engines. Background technique [0002] A gas turbine engine typically includes high and low pressure compressors, a combustor and at least one turbine. The compressor compresses the air mixed with fuel and channels it to the combustor. This mixture is then ignited to produce hot combustion gases that are channeled to a turbine that captures energy from the combustion gases to power a compressor and produce useful work to propel it through the air aircraft or power loads such as generators. [0003] The working environment within a gas turbine engine is hot and chemically hostile. Significant progress has been made in superalloys by formulating superalloys based on iron, nickel, and cobalt, although components formed from Medium time still generally does not tolerate prolonged application exp...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): C23C14/24C23C14/16C23C14/54C23C14/58C23F17/00C21D9/00F01D5/28
CPCC23C10/14C23C10/06Y02T50/67C23C10/04Y02T50/60
Inventor B·K·古普塔N·N·达斯M·D·塞洛尔R·G·小齐默曼
Owner GENERAL ELECTRIC CO