Preparation method for IC10 alloy low-pressure-turbine guide vane thermal barrier coating

A technology of thermal barrier coating and guide vane, which is applied in metal material coating process, coating, fusion spraying and other directions, can solve the problem of inability to meet the service requirements of aero-engine heterosexual blades, and achieves a simple, feasible and good spraying process method. The effect of corrosion resistance and prolonging service life

Inactive Publication Date: 2018-06-05
SHENYANG LIMING AERO-ENGINE GROUP CORPORATION
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

At present, the common preparation method for coating anti-oxidation coatings on the surface of directionally solidified alloys is the vacuum arc plating process, which cannot meet the service requirements of aeroengine heterogeneous blades

Method used

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  • Preparation method for IC10 alloy low-pressure-turbine guide vane thermal barrier coating
  • Preparation method for IC10 alloy low-pressure-turbine guide vane thermal barrier coating

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0028] Embodiment 1: The part alloy grade is IC10 alloy

[0029] In this example, it is used for the preparation method of IC10 alloy low-guide vane thermal barrier coating, and the specific steps are as follows:

[0030] Step 1: Degrease the surface of the parts, use acetone or gasoline to wipe the sprayed area of ​​the parts to remove oil and debris;

[0031] Step 2: Use pressure-sensitive tape to protect the non-sprayed area before sandblasting;

[0032] Step 3: Roughen the surface of the parts, using a press-in sand blower, 40 mesh white corundum sand to treat the area to be sprayed, and the gas pressure is 0.2MPa;

[0033] Step 4: Supersonic spray NiCrAlYSi bottom layer (the nominal composition of the bottom layer is Ni-20Cr-10Al-0.8Y-1.2Si) on the parts to be sprayed. The specific process parameters are: oxygen flow 825SCFH, current 800A, kerosene flow 6.4GPH, send Powder machine pressure 3.5bar, powder feeding rate 40g / min, spraying distance 350mm;

[0034] Step 5: C...

Embodiment 2

[0036] Embodiment 2: The part alloy grade is IC10 alloy

[0037] In this example, it is used for the preparation method of IC10 alloy low-guide vane thermal barrier coating, and the specific steps are as follows:

[0038] Step 1: Degrease the surface of the parts, use acetone or gasoline to wipe the sprayed area of ​​the parts to remove oil and debris;

[0039] Step 2: Use pressure-sensitive tape to protect the non-sprayed area before sandblasting;

[0040] Step 3: Roughen the surface of the parts, using a press-in sand blower, 60 mesh white corundum sand to treat the area to be sprayed, and the gas pressure is 0.3MPa;

[0041] Step 4: Supersonic spray NiCrAlYSi bottom layer (the nominal composition of the bottom layer is Ni-20Cr-10Al-0.8Y-1.2Si) on the parts to be sprayed. The specific process parameters are: oxygen flow 450SCFH, current 750A, kerosene flow 3.3GPH, send Powder machine pressure 2bar, powder feeding rate 25g / min, spraying distance 300mm;

[0042] Step 5: Carry...

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Abstract

The invention belongs to the technical field of aviation engine thermal barrier coatings and particularly relates to a preparation method for an IC10 alloy low-pressure-turbine guide vane thermal barrier coating. A matrix material is an IC10 directional solidified high temperature alloy, and the preparation process procedure comprises the steps of supplied part checking, preparing before spraying,spraying process parameter confirming, cleaning, protecting before grit blasting, grit blasting, protecting before spraying, a NiCrAlYSi metal bonding bottom layer supersonic spraying, a nano zirconium oxide coating atmospheric plasma spraying, clearing, final checking and respraying and repairing. According to the preparation method for the IC10 alloy low-pressure-turbine guide vane thermal barrier coating, the NiCrAlYSi metal bonding bottom layer supersonic spraying and the nano zirconium oxide coating atmospheric plasma spraying are adopted, so that the high temperature oxidation resistance and heat insulation capacities of the coating are improved, the preparation of low-pressure-turbine guide vane surface thermal barrier coating of an aviation engine of some type is realized, and bymeans of the preparation of coating, the service life of hot end components can be effectively prolonged.

Description

technical field [0001] The invention belongs to the technical field of aero-engine thermal barrier coatings, in particular to a method for preparing a thermal barrier coating for IC10 alloy low guide blades. Background technique [0002] In order to further improve the anti-oxidation and anti-corrosion properties of the directionally solidified blade, it is necessary to coat the surface of the blade with a high-temperature anti-oxidation coating. At present, the common preparation method for coating anti-oxidation coatings on the surface of directionally solidified alloys is the vacuum arc plating process, which cannot meet the service requirements of heterogeneous blades of aeroengines. Contents of the invention [0003] The purpose of the present invention is to provide a preparation method for IC10 alloy low-guide blade thermal barrier coating, which adopts supersonic spraying NiCrAlYSi bottom layer and atmospheric plasma spraying nano-zirconia surface layer, thereby im...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): C23C4/073C23C4/11C23C4/134C23C4/01C23C4/02C23C4/12
CPCC23C4/02C23C4/12
Inventor 张佳平李浩宇宋佳王璐李晓罡
Owner SHENYANG LIMING AERO-ENGINE GROUP CORPORATION
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