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In-situ generated SiC -doped Gd2Zr2O7 thermal barrier coating ceramic material and preparation method thereof

A technology of ceramic material and thermal barrier coating, applied in the field of thermal barrier coating ceramic material and its preparation, to achieve the effects of high thermal expansion coefficient, low thermal conductivity and good high temperature phase stability

Active Publication Date: 2021-07-13
江苏航运职业技术学院
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0006] But domestic and foreign related to A 2 B 2 o 7 , especially Gd 2 Zr 2 o 7 There is still a gap in the research of two-phase, three-phase or even more phase element doping of this structural material

Method used

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  • In-situ generated SiC -doped Gd2Zr2O7 thermal barrier coating ceramic material and preparation method thereof
  • In-situ generated SiC -doped Gd2Zr2O7 thermal barrier coating ceramic material and preparation method thereof
  • In-situ generated SiC -doped Gd2Zr2O7 thermal barrier coating ceramic material and preparation method thereof

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0038] a pure Gd 2 Zr 2 o 7 Ceramic materials for thermal barrier coatings.

[0039] The pure Gd 2 Zr 2 o 7 The preparation method of thermal barrier coating ceramic material is as follows:

[0040] (1) 0.039 moles of Gd 2 o 3 and 0.078 moles of ZrO 2 Heating to 500°C and holding for 5 hours for drying;

[0041] (2) Mix and dry 0.039 moles of Gd by wet high-energy ball milling 2 o 3 , 0.078 moles of ZrO 2 , ball milled for 10 hours;

[0042] (3) Take out the mixed powder, heat it in a drying oven at 120°C for 10 hours and dry it, and pass through a 300-mesh standard sampling sieve;

[0043] (4) Put the above-mentioned drying powder into a mould, put the mold into a press (diameter of 1.5cm) and press it with a pressure of 250MPa. ℃ for 12 hours, and then cooled with the furnace to prepare the above thermal barrier coating ceramic material.

[0044] Pure Gd 2 Zr 2 o 7 The thermal conductivity at 1000 degrees Celsius is 1.44176W m -1 k -1 , and its fracture t...

Embodiment 2

[0046] An in-situ SiC doped Gd 2 Zr 2 o 7 Ceramic materials for thermal barrier coatings.

[0047] The in situ generation of SiC doped Gd 2 Zr 2 o 7 Preparation method of thermal barrier coating ceramic material (TiSi 2 and graphite content are respectively 1wt% and 0.34%):

[0048] (1) 0.024 moles of Gd 2 o 3 and 0.048 moles of ZrO2 heated to 500 ° C, heat preservation for 5 hours for drying;

[0049] (2) Mix and dry 0.024 moles of Gd by wet high-energy ball milling 2 o 3 , 0.048 moles of ZrO 2 , and 0.0015 moles of TiSi 2 and 0.004 mole of graphite, ball milled for 10 hours;

[0050] (3) Take out the mixed powder, heat it in a drying oven at 120°C for 10 hours and dry it, and pass through a 300-mesh standard sampling sieve;

[0051] (4) Put the above-mentioned drying powder into a mould, put the mold into a press (diameter of 1.5cm) and press it with a pressure of 250MPa. ℃ for 12 hours, and then cooled with the furnace to prepare the above thermal barrier coa...

Embodiment 3

[0054] An in-situ SiC doped Gd 2 Zr 2 o 7 Ceramic materials for thermal barrier coatings.

[0055] The in situ generation of SiC doped Gd 2 Zr 2 o 7 Preparation method of thermal barrier coating ceramic material (TiSi 2 and graphite content are respectively 2.5wt% and 0.85wt%):

[0056] (1) 0.024 moles of Gd 2 o 3 and 0.048 moles of ZrO 2 Heating to 500°C and holding for 5 hours for drying;

[0057] (2) Mix and dry 0.024 moles of Gd by wet high-energy ball milling 2 o 3 , 0.048 moles of ZrO 2 , and 0.0036 moles of TiSi 2 and 0.01 mole of graphite, ball milled for 10 hours;

[0058] (3) Take out the mixed powder, heat it in a drying oven at 120°C for 10 hours and dry it, and pass through a 300-mesh standard sampling sieve;

[0059] (4) Put the above-mentioned drying powder into a mould, put the mold into a press (diameter of 1.5cm) and press it with a pressure of 250MPa. ℃ for 12 hours, and then cooled with the furnace to prepare the above thermal barrier coatin...

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Abstract

The invention discloses a SiC-doped Gd2Zr2O7 thermal barrier coating ceramic layer material and a preparation method thereof. The SiC-doped Gd2Zr2O7 thermal barrier coating ceramic layer material has the chemical formula of Gd2Zr2O7-XTiSi2-YC (X = 0-5 wt%, Y = 0-1.7 wt%), and the Gd2Zr2O7-XTiSi2-YC (X = 0-5 wt%, Y = 0-1.7 wt%) series thermal barrier coating ceramic layer material has the following remarkable advantages: after being doped in-situ generated second-phase substance SiC with different contents, the material has high temperature phase stability and sintering resistance at 1500 DEG C; compared with a traditional Gd2Zr2O7 thermal barrier coating ceramic material, the SiC-doped Gd2Zr2O7 thermal barrier coating ceramic layer material has the advantages that the thermal expansion coefficient at the high temperature of 1000 DEG C can reach 11 W / m.K, the thermal conductivity at the temperature of 1000 DEG C can reach 0.6-0.7 W.m-1. k-1, the fracture toughness is improved to 1.5-1.6 MPa.m1 / 2, and the SiC-doped Gd2Zr2O7 thermal barrier coating ceramic layer material has the potential to serve as a high-temperature-resistant thermal barrier coating ceramic layer material.

Description

technical field [0001] The invention belongs to the field of high temperature heat insulation protection materials, in particular to a thermal barrier coating ceramic material with high temperature resistance, low thermal conductivity, high thermal expansion coefficient and high fracture toughness and a preparation method thereof. Background technique [0002] With the continuous development of modern aviation technology, aeroengines represented by gas turbine engines are developing in the direction of high thrust-to-weight ratio, high thermal efficiency, and high flow ratio. is constantly improving. However, the existing high-temperature alloy and cooling technology cannot meet the current situation requirements. In this case, the thermal barrier coating technology with properties such as heat insulation, corrosion resistance and high temperature oxidation resistance has gradually developed to solve the problem of high temperature of engine hot end parts. One of the effect...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): C04B35/50C04B35/622C04B35/63
CPCC04B35/50C04B35/622C04B35/6303C04B2235/3244C04B2235/3891C04B2235/425C04B2235/5436C04B2235/602C04B2235/656C04B2235/6567C04B2235/96C04B2235/9607Y02T50/60
Inventor 姜伯晨曹将栋王建涛陈涵麟姚达孙萍黄健王金龙
Owner 江苏航运职业技术学院
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