Surface treatment method regulating and controlling transition interface structure of thermal barrier coating through laser shock

A laser shock and thermal barrier coating technology, applied in the field of laser applications, to achieve the effect of inhibiting the growth rate of TGO and reducing damage

Inactive Publication Date: 2018-03-27
JIANGSU UNIV
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

However, as far as the working conditions of the turbine blade are concerned, even with advanced film cooling technology, the temperature of the gas reaching the blade surface is still higher than the temperature limit of the blade alloy

Method used

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  • Surface treatment method regulating and controlling transition interface structure of thermal barrier coating through laser shock
  • Surface treatment method regulating and controlling transition interface structure of thermal barrier coating through laser shock
  • Surface treatment method regulating and controlling transition interface structure of thermal barrier coating through laser shock

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Experimental program
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Effect test

Embodiment 1

[0040] 1) Plasma spraying thermal barrier coating was carried out on the sample before nanosecond laser shock treatment, and the industrial CoCrAlYTaSi composite powder was used as the bottom layer. Plasma spray transition layer

[0041] (CoCrAlYTaSi).

[0042] 2) Use nanosecond laser beams to perform impact strengthening treatment on the surface of the bonding layer of the thermal barrier coating, and construct the macroscopic geometric structure of the bonding layer surface. The test material is GH4202 alloy, and the size of the thermal shock sample is 40×40×3mm. Second laser shock parameters: wavelength 1064nm, pulse width 23ns, energy 14J, spot diameter on the surface of the adhesive layer is about 4mm; the confinement medium is water, and a single shock treatment is implemented. Laser shock treatment leaves 3mm on each side of the sample, the center distance of the spot is 8mm, the impact area accounts for about 19.6%, 25 impact pits, and the diameter of the spherical cr...

Embodiment 2

[0045] 1) Plasma spraying thermal barrier coating was carried out on the sample before nanosecond laser shock treatment, and the industrial CoCrAlYTaSi composite powder was used as the bottom layer.

[0046] 2) Use nanosecond laser beams to perform impact strengthening treatment on the surface of the bonding layer of the thermal barrier coating, and construct the macroscopic geometric structure of the bonding layer surface. The test material is GH4202 alloy, and the size of the thermal shock sample is 40×40×3mm. Second laser shock parameters: wavelength 1064nm, pulse width 23ns, energy 18J, diameter of focused spot on the surface of the bonding layer is 4mm; the confinement medium is water, and a single shock treatment is implemented. Laser shock treatment leaves 3mm on each side of the sample, the center distance of the spot is 6mm, the impact area accounts for about 28.26%, 36 impact pits, and the diameter of the spherical crown pit is about The average height is 20 μm.

...

Embodiment 3

[0049] 1) Plasma spraying thermal barrier coating was carried out on the sample before nanosecond laser shock treatment, and the industrial CoCrAlYTaSi composite powder was used as the bottom layer.

[0050] 2) Use nanosecond laser beams to perform impact strengthening treatment on the surface of the bonding layer of the thermal barrier coating, and construct the macroscopic geometric structure of the bonding layer surface. The test material is GH4202 alloy, and the size of the thermal shock sample is 40×40×3mm. Second laser shock parameters: wavelength 1064nm, pulse width 23ns, energy 20J, diameter of focused spot on the surface of the bonding layer is 4mm; the confinement medium is water, and a single shock treatment is implemented. Laser shock treatment leaves 3mm for each side of the sample, the center distance of the spot is 0mm, the impact area accounts for about 63.58%, 81 impact pits, and the diameter of the spherical crown pit is about The average height is 30 μm.

...

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Abstract

The invention discloses a surface treatment method regulating and controlling a transition interface structure of a thermal barrier coating through laser shock. A single circular light spot is adopted, a pit is formed in the surface of a bonding material through laser shock treatment, a special geometrical morphology of the surface layer of a bonding layer is formed, thus, the bonding strength between a plasma-spray ceramic layer and the bonding layer is improved, prefabrication residual stress is formed on the surface, in the high-temperature cyclic oxidation process, thermal stress of the thermal barrier coating can be adjusted, the TGO growth speed and formation of contiguous TGO are effectively restrained, and damage of thermal stress to bonding force of the bonding layer and the ceramic layer is reduced. Through thermal shock property tests, the service life of the thermal barrier coating after bonding layer shock is greatly prolonged. The thermal barrier coating interface structure regulating method is simple in process, easy to operate and convenient to implement.

Description

technical field [0001] The invention relates to the technical field of laser application, and relates to a preparation process of an aeroengine blade thermal barrier coating. Specifically, it refers to the surface treatment method for regulating the interfacial structure of the thermal barrier coating transition layer by laser shock. Background technique [0002] The high-pressure turbine blade is the core component with the most demanding temperature and load bearing in the engine, and it is also a short board that restricts the development of the engine. At present, superalloys are the main structural materials used in high-pressure turbine blades. Among them, single crystal alloys have the highest temperature-bearing capacity, and the highest temperature they can withstand is about 1150 ° C, which is close to the temperature-bearing limit of superalloys. However, as far as the working conditions of the turbine blades are concerned, even with advanced film cooling technol...

Claims

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Application Information

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IPC IPC(8): C23C4/134C23C4/11C23C4/073C23C4/02C23C4/18
CPCC23C4/134C23C4/02C23C4/073C23C4/11C23C4/18
Inventor 花银群李志宝叶云霞帅文文张俊松陈瑞芳
Owner JIANGSU UNIV
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