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Thermal barrier coating material with low infrared transmittance and preparation method thereof

A technology of infrared transmittance and thermal barrier coating, applied in the field of thermal barrier coating, can solve the problems of inability to resist infrared radiation, phase change, etc., and achieve the effect of convenient operation, simple process and strong reliability

Active Publication Date: 2019-04-16
KUNMING UNIV OF SCI & TECH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

[0004] The purpose of the present invention is to provide a thermal barrier coating material with low infrared transmittance, which can solve the problems of phase change and inability to withstand infrared radiation at high temperature under the high temperature service condition of the thermal barrier coating of the aeroengine turbine blade. Thermal barrier coating materials with infrared transmittance, containing substances with the following mole percentages: xNiO.yEr 2 o 3 .yYb 2 o 3 .4~4.5Y 2 o 3 .88.5~94ZrO 2 , where x is 0~2, y is 1~2.5, and the total molar content of all substances is 100

Method used

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  • Thermal barrier coating material with low infrared transmittance and preparation method thereof
  • Thermal barrier coating material with low infrared transmittance and preparation method thereof
  • Thermal barrier coating material with low infrared transmittance and preparation method thereof

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Embodiment 1

[0020] A thermal barrier coating material with low infrared transmittance and a preparation method thereof, specifically comprising the following steps:

[0021] (1) The powder raw material ZrO 2 , Y 2 o 3 , NiO, Er 2 o 3 , Yb 2 o 3 Place in a resistance furnace at a rate of 5°C / min to 1000°C and bake for 2 hours, then cool to room temperature with the furnace to remove the moisture and CO adsorbed in the oxide raw material 2 , to obtain dry powder raw material;

[0022] (2) Accurately and quickly weigh the mass of each oxide after pretreatment according to the designed stoichiometric ratio, wherein the molar ratio of each powder raw material is NiO:Er 2 o 3 : Yb 2 o 3 : Y 2 o 3 : ZrO 2 =0:1.0:1.0:4.0:94, mix and put into a ball mill jar, add a certain amount of zirconia balls, absolute ethanol and oxide according to the mass ratio of 4:3:1, to obtain a mixture;

[0023] (3) The mixture was mechanically ball milled for 6 hours, evaporated to dryness, and dried in...

Embodiment 2

[0029] A thermal barrier coating material with low infrared transmittance and a preparation method thereof, specifically comprising the following steps:

[0030] (1) The powder raw material ZrO 2 , Y 2 o 3 , NiO, Er 2 o 3 , Yb 2 o 3 Place in a resistance furnace at a rate of 5°C / min to 1000°C and bake for 2 hours, then cool to room temperature with the furnace to remove the moisture and CO adsorbed in the oxide raw material 2 , to obtain dry powder raw material;

[0031] (2) Accurately and quickly weigh the mass of each oxide after pretreatment according to the designed stoichiometric ratio, wherein the molar ratio of each powder raw material is NiO:Er 2 o 3 : Yb 2 o 3 : Y 2 o 3 : ZrO 2 =1.0:2.0:2.0:4.2:90.8, mix and put it into a ball mill jar, add a certain amount of zirconia balls, absolute ethanol and oxide according to the mass ratio of 4:3:1, to obtain a mixture;

[0032] (3) The mixture was mechanically ball milled for 10 hours, evaporated to dryness, and ...

Embodiment 3

[0038] A thermal barrier coating material with low infrared transmittance and a preparation method thereof, specifically comprising the following steps:

[0039] (1) The powder raw material ZrO 2 , Y 2 o 3 , NiO, Er 2 o 3 , Yb 2 o 3 Place in a resistance furnace at a rate of 5°C / min to 1000°C and bake for 2 hours, then cool to room temperature with the furnace to remove the moisture and CO adsorbed in the oxide raw material 2 , to obtain dry powder raw material;

[0040] (2) Accurately and quickly weigh the mass of each oxide after pretreatment according to the designed stoichiometric ratio, wherein the molar ratio of each powder raw material is NiO:Er 2 o3 : Yb 2 o 3 : Y 2 o 3 : ZrO 2 =2.0:2.5:2.5:4.5:88.5, mix and put into a ball mill jar, add a certain amount of zirconia balls, absolute ethanol and oxide according to the mass ratio of 4:3:1, to obtain a mixture;

[0041] (3) The mixture was mechanically ball milled for 8 hours, evaporated to dryness, and dried ...

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Abstract

The invention discloses a thermal barrier coating material with low infrared transmittance and a preparation method thereof, and belongs to the field of thermal barrier coating materials. The thermalbarrier coating material comprises, by mole, the following components: xNiO-yEr2O3-yYb2O3-4-4.5Y2O3-88.5-94ZrO2, wherein the molar total content of all substances is 100, x is 0-2, and y is 1-2.5. Theinfrared transmittance of the thermal barrier coating material with low infrared transmittance is reduced by about 20-30% compared with that of YSZ, the original phase structure can be maintained under the condition of high-temperature long-time heat preservation, the thermal conductivity is reduced by about 18-20% compared with that of YSZ, excellent heat insulation performance is maintained, and the material can meet the requirement of long-term service of thermal barrier coatings of thermal end parts of aero engines and ground gas turbines at high temperature.

Description

technical field [0001] The invention relates to a thermal barrier coating material with low infrared transmittance and a preparation method thereof, belonging to the field of thermal barrier coatings. Background technique [0002] Thermal barrier coatings have the characteristics of high temperature resistance and low thermal conductivity. When applied to high-pressure turbine blades of aero-engines, they can significantly reduce the surface temperature of turbine blade alloys, greatly extend the working life of blades, and improve engine thrust and efficiency. The traditional thermal barrier coating material uses yttria-stabilized zirconia, that is, 6-8wt% YSZ, which has excellent comprehensive performance. However, when the temperature exceeds 1200°C, a phase transition will occur, and the thermal conductivity is relatively high. Furthermore, with the increase of the thrust-to-weight ratio of aero-engines, infrared radiation cannot be resisted at high temperatures. YSZ is...

Claims

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Application Information

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IPC IPC(8): C04B35/48C04B35/622
CPCC04B35/48C04B35/622C04B2235/3279C04B2235/3225C04B2235/3224C04B2235/9607C04B2235/96C04B2235/6567C04B2235/6562
Inventor 吴煦王开军胡劲李闯
Owner KUNMING UNIV OF SCI & TECH
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