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Yb modified CMAS prevention composite structure thermal barrier coating and preparing method thereof

A technology of thermal barrier coating and composite structure, which is applied in the direction of coating, metal material coating process, superimposed layer plating, etc., and can solve problems such as low thermal conductivity, easy expansion of coating cracks, and short thermal cycle life

Active Publication Date: 2020-07-31
BEIHANG UNIV
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  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

Among the thermal barrier coating materials studied for high-temperature service environments above 1300°C, rare earth zirconates have low thermal conductivity (~1.2W / (m*K)), high phase stability (room temperature~1600°C), and YSZ close thermal expansion coefficient (TEC: 10.5*10 -6 K -1 ), strong anti-sintering performance and other characteristics, it has become one of the most potential materials. However, the disadvantages of rare earth zirconates are also obvious, such as low fracture toughness, easy expansion of coating cracks, short thermal cycle life, and In actual service, especially when the temperature exceeds 1300 °C, the existence of CMAS becomes a key factor that threatens the life of thermal barrier coatings

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  • Yb modified CMAS prevention composite structure thermal barrier coating and preparing method thereof
  • Yb modified CMAS prevention composite structure thermal barrier coating and preparing method thereof

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preparation example Construction

[0044] Based on the same inventive concept, the present invention also provides a preparation method of Yb modified anti-CMAS composite structure thermal barrier coating, such as figure 2 shown, including the following steps:

[0045] S1: preparing a bonding layer on the surface of the substrate;

[0046] Specifically, the substrate can be a superalloy substrate; before preparing the bonding layer, the surface of the superalloy substrate can be polished with sandpaper, then the polished superalloy substrate can be ultrasonically cleaned in alcohol or acetone, and finally the superalloy substrate The surface is pretreated by wet sandblasting to roughness Ra≤3; the bonding layer can be treated by one or more of multi-arc ion plating, low-pressure plasma spraying, magnetron sputtering, vapor phase infiltration, embedding infiltration, electroplating, and vapor phase deposition. A combination of the above methods is formed, and the formed bonding layer is subjected to vacuum hea...

Embodiment 1

[0065] The first step is to prepare single-phase fluorite structure ytterbium zirconate material and spray powder

[0066] (1) According to the chemical structural formula (Gd 1-x1 Yb x1 ) 2 Zr 2 o 7 and (Gd 1-x2 Yb x2 ) 2 Zr 2 o 7 , where, x1=0.2, x2=0.4, respectively weigh the high-purity oxide Gd 2 o 3 Powder, Yb 2 o 3 Powder and ZrO 2 Powder, two groups of weighed powders are mixed separately to obtain two kinds of mixed slurry;

[0067] (2) Put the above two kinds of mixed slurry into an oven to dry at a temperature of 60°C for 5h to 10h, then put it into a high-temperature furnace, and raise it to 1500°C in an air atmosphere for a high-temperature phase-forming reaction, and the reaction time For 15h, with furnace cooling, respectively (Gd 0.8 Yb 0.2 ) 2 Zr 2 o 7 and (Gd 0.6 Yb 0.4 ) 2 Zr 2 o 7 two materials;

[0068] (3) The above (Gd 0.8 Yb 0.2 ) 2 Zr 2 o 7 and (Gd 0.6 Yb 0.4 ) 2 Zr 2 o 7 The two materials were crushed by ball milling...

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Abstract

The invention discloses an Yb modified CMAS prevention composite structure thermal barrier coating and a preparing method thereof. A CMAS corrosion prevention layer adopts Yb modified rare earth zirconate to form a compact layered structure, at the high temperature, the layered structure can have a reaction with CMAS to form a compact blocking layer, permeation of molten CMAS to the interior of the thermal barrier coating can be prevented, a first heat insulation layer adopts Yb modified rare earth zirconate to form a columnar structure, enough heat insulation performance and high strain tolerance can be provided for the thermal barrier coating, the thermal shock property of the thermal barrier coating is improved, the service life of the thermal barrier coating can be prolonged, the CMAScorrosion prevention layer and the first heat insulation layer are made of materials of the same elements, heat mis-match stress between the two layers can be relieved, combining strength of the two layers can be improved, the thermal barrier coating has the advantages of being low in heat conduction rate, stable in phase, high in combining strength, and high in sintering resisting capacity, the service life under the high-temperature service condition is long, combination strength between dual layers of ceramic can be high, and combination strength between a ceramic layer and a metal bondinglayer is high.

Description

technical field [0001] The invention relates to the technical field of high-temperature ceramic materials and thermal barrier coatings, in particular to a Yb-modified anti-CMAS composite structure thermal barrier coating and a preparation method thereof. Background technique [0002] Thermal barrier coatings (Thermal Barrier Coatings, TBCs) are commonly used on the hot end components of advanced gas turbine engines. So far, the most widely used ceramic layer material is 8YSZ (6~8wt.% yttrium oxide stabilized zirconia), with a melting point of 2700°C, a thermal conductivity of 2.6W / (m*K), and a thermal expansion coefficient TEC: 11 *10 -6 K -1 , fracture toughness ~ 3MPa, when the temperature exceeds 1250°C, the material will undergo phase transformation, making the thermal barrier coating sintered and brittle and fall off, making it impossible to serve at temperatures above 1250°C; in addition, with the engine working With the increase of temperature, volcanic ash (the ma...

Claims

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Application Information

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IPC IPC(8): C23C28/00C23C4/11C23C4/131C23C4/134
CPCC23C28/3455C23C4/11C23C4/131C23C4/134
Inventor 郭洪波李珊何雯婷宫声凯徐惠彬
Owner BEIHANG UNIV
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