Preparation method of high temperature CMAS and rain corrosion-resistant composite thermal barrier coating

A technology of thermal barrier coating and high temperature resistance, applied in coating, metal material coating process, fusion spraying, etc., can solve problems such as film cracking, shortening the service life of thermal barrier coating, and large difference in thermal expansion coefficient. Achieve cost reduction, improve CMAS corrosion resistance, and improve corrosion resistance

Inactive Publication Date: 2020-01-03
HEBEI UNIV OF TECH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

[0004] However, when the coating is oxidized at high temperature, the NiCoCrAlY alloy will be selectively oxidized, and a thermally grown oxide (TGO) layer will be formed on the surface, and its composition is mainly Al 2 o 3 , wh

Method used

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  • Preparation method of high temperature CMAS and rain corrosion-resistant composite thermal barrier coating
  • Preparation method of high temperature CMAS and rain corrosion-resistant composite thermal barrier coating
  • Preparation method of high temperature CMAS and rain corrosion-resistant composite thermal barrier coating

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Experimental program
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Effect test

Embodiment 1

[0037] Step 1: Formulating Gd for Plasma Spraying 2 Zr 2 o 7 / Al 2 o 3 compound powder;

[0038] Gd with a particle size ranging from 15 to 30 microns 2 Zr 2 o 7 Powder, Al with particle size ranging from 0.06 to 1 micron 2 o 3 The powder is evenly mixed into a mixed powder. Among them, Al 2 o 3 Powder accounted for 10% by mass of the total mass of raw material powder, Gd 2 Zr 2 o 7 Powder accounted for 90% by mass of the total mass of raw material powder, Gd 2 Zr 2 o 7 and Al 2 o 3 The mass ratio between them is 90:10, and then uniformly mixed into the mass percentage is mixed powder: polyvinyl alcohol = 99:1 binder, mechanically mixed and stirred for 100 minutes, and then ultrasonically oscillated for 20 minutes. This is formulated as Gd for plasma spraying 2 Zr 2 o 7 / Al 2 o 3 compound powder;

[0039] The second step: pretreatment of metal matrix materials:

[0040] Sandblasting is performed on the surface of the GH3044 nickel-based superalloy to ...

Embodiment 2

[0051] Step 1: Formulating Gd for Plasma Spraying 2 Zr 2 o 7 / Al 2 o 3 compound powder;

[0052] Gd with a particle size ranging from 15 to 30 microns 2 Zr 2 o 7 Powder, Al with particle size ranging from 0.06 to 1 micron 2 o 3 The powder is evenly mixed into a mixed powder. Among them, Al 2 o 3 Powder accounted for 15% by mass of the total mass of raw material powder, Gd 2 Zr 2 o 7 Powder accounted for 85% by mass of the total mass of raw material powder, Gd 2 Zr 2 o 7 and Al 2 o 3 The mass ratio between them is 85:15, and then uniformly mixed into the mass percentage of powder: polyvinyl alcohol = 99:1 binder, mechanically mixed and stirred for 100 minutes, and then ultrasonically oscillated for 20 minutes, thus Formulated as Gd for plasma spraying 2 Zr 2 o 7 / Al 2 o 3 compound powder;

[0053] The second step: pretreatment of metal matrix materials:

[0054] The surface of the GH3044 nickel-based superalloy to be coated is sandblasted, and then the...

Embodiment 3

[0060] Step 1: Formulating Gd for Plasma Spraying 2 Zr 2 o 7 / Al 2 o 3 compound powder;

[0061] Gd with a particle size ranging from 15 to 30 microns 2 Zr 2 o 7 Powder, Al with particle size ranging from 0.06 to 1 micron 2 o 3 The powder is evenly mixed into a mixed powder. Among them, Al 2 o 3 Powder accounted for 20% by mass of the total mass of raw material powder, Gd 2 Zr 2 o 7 Powder accounted for 80% by mass of the total mass of raw material powder, Gd 2 Zr 2 o 7 and Al 2 o 3 The mass ratio between them is 80:20, and then uniformly mixed into the mass percentage of powder: polyvinyl alcohol = 99:1 binder, mechanically mixed and stirred for 100 minutes, and then ultrasonically oscillated for 20 minutes, thus Formulated as Gd for plasma spraying 2 Zr 2 o 7 / Al 2 o 3 compound powder;

[0062] The second step: pretreatment of metal matrix materials:

[0063] The surface of the GH3044 nickel-based superalloy to be coated is sandblasted, and then the...

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Abstract

The present invention relates to a preparation method of a high temperature CMAS and rain corrosion-resistant composite thermal barrier coating. The method includes the following steps: step 1: mechanically mixing Gd2Zr2O7 powder and Al2O3 powder to form mixed powder, then adding a binder, stirring and performing ultrasonic shaking to obtain Gd2Zr2O7/Al2O3 composite powder; step 2: performing sandblasting to the surface of the metallic matrix material of the desired coating, then coating a bonding layer on the surface of the metallic matrix material after sand blasting, and completing pre-treatment to the metallic matrix material; and step 3: using a method of plasma coating to spray the Gd2Zr2O7/Al2O3 composite powder to the surface of the metallic matrix material so as to form a Gd2Zr2O7/Al2O3 composite coating. The preparation method of the present invention improves the high-temperature resistance and corrosion resistance of the thermal barrier coating, and overcomes the performance defect of the coating under high temperature CMAS and rain corrosion.

Description

technical field [0001] The design scheme of the present invention involves using Gd 2 Zr 2 o 7 / Al 2 o 3 Plating of nickel-based superalloys, specifically a Gd 2 Zr 2 o 7 / Al 2 o 3 Preparation method of composite coating. Background technique [0002] With the development of my country's aerospace industry and the increasing demand for flight speed, flight distance and safety performance during spaceflight, gas turbine engines are developing towards high thrust-to-weight ratio, high efficiency, low fuel consumption and long life. At present, nickel-based superalloys and ceramic-based composite materials are high-temperature structural materials for manufacturing engine blades, but their maximum temperature is only about 1150°C. Therefore, the emergence of thermal barrier coating technology has largely solved this problem. . At present, thermal barrier coating technology has been listed as one of the three key technologies of high-pressure turbine blade manufacturi...

Claims

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Application Information

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IPC IPC(8): C23C4/134C23C4/11
CPCC23C4/11C23C4/134
Inventor 董天顺刘琦冯阳李国禄付彬国李艳姣
Owner HEBEI UNIV OF TECH
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