Ultralow-thermal-conductivity stable-high-temperature-phase neodymium-cerium compounded zirconate thermal barrier coating material and preparation method thereof

A technology of compounding zirconate and thermal barrier coating, applied in the field of thermal barrier coating, can solve the problem that the field of thermal barrier coating has not been paid attention to, and achieves improved thermal insulation effect, low thermal conductivity, high and high temperature phase stability Effect

Inactive Publication Date: 2017-03-22
SOUTHWEAT UNIV OF SCI & TECH
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  • Abstract
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Problems solved by technology

[0006] Cerium zirconate Ce 2 Zr 2 o 7+x (x=0~1) and Ln 2 Zr 2 o 7 It has a similar crystal structure [J.B.Thomson et al., J.Am.Ceram.Soc., 118, 11129 (1996)], but it is easy to decompose into two phases of cerium-rich and cerium-poor at 1200°C [M.Yashima et al .,J.Am.Ceram.Soc.,77,1067(1994)], has not received much attention in the field of thermal barrier coatings

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  • Ultralow-thermal-conductivity stable-high-temperature-phase neodymium-cerium compounded zirconate thermal barrier coating material and preparation method thereof
  • Ultralow-thermal-conductivity stable-high-temperature-phase neodymium-cerium compounded zirconate thermal barrier coating material and preparation method thereof
  • Ultralow-thermal-conductivity stable-high-temperature-phase neodymium-cerium compounded zirconate thermal barrier coating material and preparation method thereof

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preparation example Construction

[0033] According to one aspect of the present invention, the method for preparing the neodymium-cerium composite zirconate thermal barrier coating material is characterized by comprising:

[0034] With a purity of 99.99% Nd(NO 3 ) 3 ·6H 2 O, Ce(NO 3 ) 3 ·6H 2 O, Zr(NO 3 ) 4 ·3H 2 O is the raw material, massage Erbi Nd(NO 3 ) 3 ·6H 2 O: Ce(NO 3 ) 3 ·6H 2 O: Zr(NO 3 ) 4 ·3H 2 O=(0.2-0.8):(0.2-0.8):1 Weigh, prepare an aqueous solution with a total energy concentration of metal ions of 0.1 mol / L, add citric acid and polyethylene glycol as additives, and add 50 g / L Liter, 30 g / liter, magnetically stirred to a clear and transparent sol,

[0035] Using air with a purity of 99.99% and a pressure of 0.1 MPa as the atomizing medium, the sol is atomized to a corundum crucible at 400°C to quickly remove water to obtain the neodymium-cerium composite zirconate thermal barrier coating material precursor. It is calcined in an air atmosphere at 1200°C for 6 hours and then cooled to room temperatur...

Embodiment 1

[0038] With a purity of 99.99% Nd(NO 3 ) 3 ·6H 2 O, Ce(NO 3 ) 3 ·6H 2 O, Zr(NO 3 ) 4 ·3H 2 O is the raw material, massage Erbi Nd(NO 3 ) 3 ·6H 2 O: Ce(NO 3 ) 3 ·6H 2 O: Zr(NO 3 ) 4 ·3H 2 O=0.2:0.8:1 Weigh, prepare an aqueous solution with a total energy concentration of metal ions of 0.1mol / L, add citric acid and polyethylene glycol as additives, and add 50 g / L and 30 g / L respectively. Magnetic force Stir for 0.5 hours to obtain a clear and transparent sol.

[0039] Using air with a purity of 99.99% and a pressure of 0.1 MPa as the atomizing medium, the sol is atomized into a corundum crucible at a temperature of 400°C to quickly remove moisture, and then calcined in an air atmosphere at 1200°C for 6 hours and then cooled to room temperature. (Ce 0.8 Nd 0.2 ) 2 Zr 2 O 7.8 powder.

[0040] Put the above synthesized powder into an agate mortar and grind it, take an appropriate amount into a stainless steel mold with a diameter of 18mm, and press it into a shape under a pressure of 50...

Embodiment 2

[0048] With a purity of 99.99% Nd(NO 3 ) 3 ·6H 2 O, Ce(NO 3 ) 3 ·6H 2 O, Zr(NO 3 ) 4 ·3H 2 O is the raw material, massage Erbi Nd(NO 3 ) 3 ·6H 2 O: Ce(NO 3 ) 3 ·6H 2 O: Zr(NO 3 ) 4 ·3H 2 Weigh O=0.5:0.5:1, prepare an aqueous solution with a total energy concentration of metal ions of 0.1 mol / L, add citric acid and polyethylene glycol as additives, and add 50 g / l and 30 g / l, respectively. Magnetic force Stir for 0.5 hours to obtain a clear and transparent sol.

[0049] Using air with a purity of 99.99% and a pressure of 0.1MPa as the atomizing medium, the sol is atomized into a corundum crucible at a temperature of 400℃ to quickly remove water to obtain a precursor, which is then calcined in an air atmosphere at 1200℃ for 6 hours and then cooled To room temperature to obtain (Ce 0.5 Nd 0.5 ) 2 Zr 2 O 7.5 powder.

[0050] Put the above synthesized powder into an agate mortar and grind, take an appropriate amount into a stainless steel mold with a diameter of 18mm, and press it into a...

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Abstract

The invention discloses an ultralow-thermal-conductivity stable-high-temperature-phase neodymium-cerium compounded zirconate thermal barrier coating material and a preparation method thereof. The thermal conductivity of the material is 60% lower or more than 60% lower than that of an existing thermal barrier coating material, and is also lower than the thermal conductivity of a rare earth zirconate material of the same kind; and on the other hand, no phase changes are generated within the interval between the room temperature and 1600 DEG C. The material is more beneficial to increase of the thermal simulation effect and working temperature of the thermal barrier coating, and can be used for the aerospace fields of aviation turbine engines, gas turbines, hypersonic-speed cruise missile hot end parts and the like.

Description

Technical field [0001] The invention relates to a neodymium-cerium composite zirconate thermal barrier coating material with ultra-low thermal conductivity and high temperature phase stability and a preparation method thereof, belonging to the field of thermal barrier coatings. Background technique [0002] Thermal Barrier Coatings (TBCs) are ceramic coatings deposited on the surface of high-temperature resistant metals with good thermal insulation effect [NPPadture et al., Science,296,280(2002)], which can make the base alloy material It is protected from high temperature oxidation and corrosion, and can reduce the working temperature of the substrate surface, improve the fuel combustion efficiency, and can greatly extend the life of the engine. It has important applications in the fields of aviation gas turbine engines, gas turbines, and hypersonic cruise bombs. value. Increasing the gas inlet temperature can increase the engine thrust-to-weight ratio, improve the heat engine ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): C04B35/48C04B35/622
CPCC04B35/48C04B35/622C04B2235/3224C04B2235/3229C04B2235/9607
Inventor 王欣江阔江海洋刘松柏
Owner SOUTHWEAT UNIV OF SCI & TECH
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