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Preparation method of high-entropy rare earth aluminate thermal protection coating

A technology of aluminate and heat protection, applied in coating, metal material coating process, fusion spraying, etc., can solve problems such as easy peeling, heat protection coating cannot meet high temperature service conditions, etc., to reduce porosity, The effect of alleviating premature peeling failure and improving thermal cycle life

Pending Publication Date: 2022-07-22
ZHENGZHOU UNIV
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  • Summary
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  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] Aiming at the problem that the current thermal protective coating cannot meet the high-temperature service conditions and is easy to peel off under the action of thermal load, the present invention provides a preparation method of a high-entropy rare earth aluminate thermal protective coating. By optimizing the process conditions, low porosity can be obtained High entropy rare earth aluminate ceramic thermal protective coating with high rate, high deposition rate and good thermal shock resistance, which can meet the long-term use requirements under high temperature service conditions

Method used

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  • Preparation method of high-entropy rare earth aluminate thermal protection coating

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Experimental program
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Effect test

Embodiment 1

[0043] (1) Clean the surface to be sprayed of the GH4169 superalloy substrate with analytically pure acetone to remove impurities such as dust and oil stains attached to the surface of the substrate, and then use 40-mesh to 80-mesh corundum sand to blast the surface of the substrate to be sprayed. , so that the surface roughness of the substrate reaches Ra=5μm, and the corundum sand particles remaining on the surface of the substrate are blown clean with compressed air;

[0044] (2) First preheat the substrate to 200°C, and then use the atmospheric plasma spraying process to spray NiCrCoAlY powder with a particle size of 30 μm to 75 μm on the substrate to form a NiCrCoAlY bonding layer with a thickness of 0.1 mm;

[0045] Among them, the atmospheric plasma spraying process parameters for preparing the NiCrCoAlY bonding layer are as follows: the spraying angle is 90°, the spraying distance is 75mm, the current is 500A, the voltage is 65V, the flow rate of the working gas (Ar) is...

Embodiment 2

[0051] (1) Clean the surface to be sprayed of the GH4169 superalloy substrate with analytically pure acetone to remove impurities such as dust and oil stains attached to the surface of the substrate, and then use 40-mesh to 80-mesh corundum sand to blast the surface of the substrate to be sprayed. , so that the surface roughness of the substrate reaches Ra=6μm, and the corundum sand particles remaining on the surface of the substrate are blown clean with compressed air;

[0052] (2) First preheat the substrate to 200°C, and then use the atmospheric plasma spraying process to spray NiCrCoAlY powder with a particle size of 30 μm to 75 μm on the substrate to form a NiCrCoAlY bonding layer with a thickness of 0.1 mm;

[0053] Among them, the atmospheric plasma spraying process parameters for preparing the NiCrCoAlY bonding layer are as follows: the spraying angle is 90°, the spraying distance is 75mm, the current is 500A, the voltage is 65V, the flow rate of the working gas (Ar) is...

Embodiment 3

[0061](1) Clean the surface to be sprayed of the GH4169 superalloy substrate with analytically pure acetone to remove impurities such as dust and oil stains attached to the surface of the substrate, and then use 40-mesh to 80-mesh corundum sand to blast the surface of the substrate to be sprayed. , so that the surface roughness of the substrate reaches Ra=6μm, and the corundum sand particles remaining on the surface of the substrate are blown clean with compressed air;

[0062] (2) First preheat the substrate to 200°C, and then use the atmospheric plasma spraying process to spray NiCrCoAlY powder with a particle size of 30 μm to 75 μm on the substrate to form a NiCrCoAlY bonding layer with a thickness of 0.1 mm;

[0063] Among them, the atmospheric plasma spraying process parameters for preparing the NiCrCoAlY bonding layer are as follows: the spraying angle is 90°, the spraying distance is 75mm, the current is 500A, the voltage is 65V, the flow rate of the working gas (Ar) is ...

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Abstract

The invention relates to a preparation method of a high-entropy rare earth aluminate thermal protection coating, and belongs to the technical field of thermal protection coatings. The preparation method comprises the following steps: firstly, preparing a NiCrCoAlY bonding layer on a substrate with the surface roughness of 4-8 microns by adopting a thermal spraying process, and then, directly preparing a high-entropy rare earth aluminate layer on the NiCrCoAlY bonding layer by adopting an atmospheric plasma spraying process, or firstly, preparing a YSZ or Al2O3 intermediate layer on the NiCrCoAlY bonding layer by adopting the thermal spraying process, and then, preparing the high-entropy rare earth aluminate layer on the NiCrCoAlY bonding layer by adopting the high-entropy rare earth aluminate layer on the NiCrCoAlY bonding layer by adopting the high-entropy rare earth aluminate layer. And preparing a high-entropy rare earth aluminate layer on the intermediate layer by adopting an atmospheric plasma spraying process, so as to form the high-entropy rare earth aluminate thermal protection coating on the substrate. According to the method disclosed by the invention, the high-entropy rare earth aluminate ceramic thermal protection coating with low porosity, high deposition rate and good thermal shock resistance can be obtained by optimizing process conditions, and the requirement of long-term use under a high-temperature service condition can be met.

Description

technical field [0001] The invention relates to a preparation method of a high-entropy rare earth aluminate thermal protective coating, belonging to the technical field of thermal protective coatings. Background technique [0002] With the development of aerospace gas turbines in the direction of high flow ratio, high thrust-to-weight ratio, and high inlet temperature, the gas temperature and pressure in the combustion chamber continue to increase. At present, the widely used thermal protective coating (TPC) material is yttrium oxide partially stabilized zirconia (YSZ). Since the long-term use temperature of YSZ is lower than 1200 °C, it can no longer meet the needs of future technological development. In addition, in order to further increase the operating temperature of jet and gas turbine engines, thermal conductivity needs to be reduced. Therefore, there is an urgent need to develop new TPC materials with good high temperature stability and low thermal conductivity. ...

Claims

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Application Information

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IPC IPC(8): C23C4/134C23C4/073C23C4/02C23C4/11
CPCC23C4/134C23C4/073C23C4/02C23C4/11
Inventor 朱锦鹏汪凯伦王海龙杨凯军李明亮舒永春何季麟
Owner ZHENGZHOU UNIV
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