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 technolo

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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Example Embodiment

[0039] Example 1

[0040] 1) Plasma spraying thermal barrier coating on the sample before nanosecond laser shock treatment, with industrial CoCrAlYTaSi composite powder as the bottom layer. Plasma sprayed transition layer

[0041] (CoCrAlYTaSi).

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

Example Embodiment

[0044] Example 2

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

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

[0047] 3) Take industrial ZrO 2...

Example Embodiment

[0048] Example 3

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

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

[00...

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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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