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Process for removing thermal barrier coatings

A thermal resistance, coating technology, applied in the direction of coating, metal material coating process, sustainable transportation, etc., can solve problems such as increased wear and erosion

Inactive Publication Date: 2007-01-10
TURBOCOMBUSTOR TECH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

Increased circulation and / or increased pressure increases wear and erosion

Method used

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  • Process for removing thermal barrier coatings

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[0019] The high temperature part of the jet engine combustion chamber (which is made of nickel or cobalt based superalloy material) is laser punched with air cooling holes during manufacture. The surface of this part of the gas passage (high temperature side) is first coated with a metal bonding layer, which is mainly nickel and contains chromium, aluminum and yttrium oxide (or another reactive element). The metal bonding layer is applied by a plasma spray process to a thickness, typically about 0.005 to 0.008 inches (about 0.13 to 0.020 mm). After the bonding layer is applied, the air cooling holes are laser drilled to generate the required angle of incidence to achieve the desired air cooling characteristics of the part. After laser drilling, the part is cleaned to remove laser slag, or waste material from the laser drilling process. After laser drilling and cleaning, a bond coat of approximately 0.001 to 0.003 inches thick can be applied by a plasma spray process, optional...

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Abstract

Briefly, the present invention provides a process which uses an air jet containing non-abrasive particulate media at a low pressure which selectively removes thermal barrier coatings from components without damaging the metallic substrate. This process selectively removes thermal barrier coatings from the cooling holes of components.

Description

technical field [0001] The present invention relates generally to a method for removing thermally resistant coatings from metal parts, and more particularly to a method for removing thermally resistant ceramic coatings from gas turbine engine components such as cooling holes of combustor liners. Background technique [0002] Gas turbine engines (aerospace and industrial) are designed so that their nickel-cobalt superalloy components can operate at temperatures around their melting point. The important function of Thermal Barrier Coating (TBC) is to thermally insulate components that operate at high temperatures. A typical turbine component has a combustion chamber (see figure 1 Combustion chamber 10), ducts, exhaust nozzles, turbine blades and nozzle guide vanes. TBCs are characterized by their low thermal conductivity and the coating exhibits large temperature gradients when exposed to heat flow. [0003] The most common TBC material is yttria-stabilized zirconia (YSZ), ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B23P15/02B23P6/00
CPCC23C4/005Y10T29/49318Y10T29/49995B23P2700/06Y10T29/4533Y10T29/455B23P6/002Y10T29/49885Y10T29/49341C23C4/01Y02T50/60
Inventor 盖伊·林·汉利
Owner TURBOCOMBUSTOR TECH
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