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Preparation method of composite rare earth zirconate thermal barrier coating ceramic material

A thermal barrier coating, ceramic material technology

Inactive Publication Date: 2011-05-11
HARBIN INST OF TECH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] The purpose of the present invention is to solve the problem of severe phase transition, high thermal conductivity and low thermal expansion coefficient of existing thermal barrier coating ceramic materials when the temperature exceeds 1200 °C etc., and provide a preparation method of composite rare earth zirconate thermal barrier coating ceramic material

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  • Preparation method of composite rare earth zirconate thermal barrier coating ceramic material
  • Preparation method of composite rare earth zirconate thermal barrier coating ceramic material

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Experimental program
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specific Embodiment approach 1

[0014] In this embodiment, the thermal conductivity and thermal expansion coefficient of the composite rare earth zirconate thermal barrier coating ceramic material prepared by selecting different raw material components at 1400°C are shown in Table 1.

[0015] Table 1

[0016] chemical formula

Thermal conductivity (W·m -1 ·K -1 , 1400℃)

Coefficient of thermal expansion (K -1 , 1400℃)

(Nd 0.1 Yb 0.9 ) 2 Zr 2 o 7

1.61

10.6×10 -6

(Nd 0.3 Yb 0.7 ) 2 Zr 2 o 7

1.50

10.6×10 -6

(Nd 0.5 Yb 0.5 ) 2 Zr 2 o 7

1.46

10.8×10 -6

(Nd 0.7 Yb 0.3 ) 2 Zr 2 o 7

1.58

11.0×10 -6

(Nd 0.9 Yb 0.1 ) 2 Zr 2 o 7

1.55

11.4×10 -6

(Sm 0.1 Yb 0.9 ) 2 Zr 2 o 7

1.48

10.9×10 -6

(Sm 0.3 Yb 0.7 ) 2 Zr 2 o 7

1.48

11.1×10 -6

(Sm 0.5 Yb 0.5 ) 2 Zr 2 o 7

1.50

11.4×10 -6

[00...

specific Embodiment approach 2

[0021] The purpose of adding deionized water in step 2 of this embodiment is to make the mixed powder mix more uniformly.

specific Embodiment approach 3

[0022] In step 2 of this embodiment, zirconia ceramic balls with a diameter of 5 mm, 10 mm or 15 mm are used as grinding media for ball milling.

[0023] The molecular formula of the composite rare earth zirconate thermal barrier coating ceramic material obtained in this embodiment is (Ln x Yb 1-x ) 2 Zr 2 o 7 .

[0024]Embodiment 4: The difference between this embodiment and Embodiment 3 is that in Step 4, the dried mixed powder is put into the air atmosphere, and the temperature is raised from room temperature to 1100-1150°C at a heating rate of 5°C / min. , and thermally heat-treated for 6-10 hours, then cooled to room temperature, and ball milled for 23-25 ​​hours. Other steps and parameters are the same as those in the third embodiment.

[0025] Embodiment 5: The difference between this embodiment and Embodiment 3 is that in Step 5, the powder A is heated from room temperature to 1275-1300°C at a heating rate of 5°C / min, and heat-insulated and heat-treated for 4-10 ho...

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Abstract

The present invention provides a method for preparing composite rare earth zirconate thermal barrier ceramic material, and relates to the thermal barrier coating ceramic material and the preparation method. The preparation method solves the problems of complex process, high cost, serious phase change at the temperature above 1200 DEG C, high thermal conductivity, low coefficient of thermal expansion and so on in the prior preparation method of the thermal barrier coating ceramic material. The composite rare earth zirconate thermal barrier ceramic material is made of zirconia, rare earth oxide Ln2O3 and rare earth oxide Yb2O3. The preparation method comprises the following steps: 1, the zirconia, the rare earth oxide Ln2O3 and the rare earth oxide Yb2O3 are mixed; 2, deionized water is added for ball milling and the dried mixed powder can be prepared after drying; 3, powder C can be prepared after a plurality of processing steps; 4, the powder C is cooled and molded by isostatic pressing to prepare a green body; 5, the green body is sintered to prepare the composite rare earth zirconate thermal barrier ceramic material. The preparation method has the advantages of simple process, low cost, no phase change of the product at high temperature, low thermal conductivity and high coefficient of thermal expansion.

Description

technical field [0001] The invention relates to a preparation method of a thermal barrier coating ceramic material Background technique [0002] With the rapid development of the aerospace industry, the engine is rapidly developing towards a high thrust-to-weight ratio, and the inlet temperature of the turbine blades is also increasing. For engines developed abroad in the 1970s, the gas inlet temperature in front of the turbine blades had reached above 1300°C; in the 1990s, the gas inlet temperature in front of the turbine blades had reached 1550°C to 1650°C. In order to adapt to such a high gas temperature, there are three corresponding measures: one is to develop more advanced high-temperature single crystal alloy materials; the other is to further improve the cooling technology; the third is to develop high-performance thermal barrier coating ceramic materials. At present, the development of superalloys for the first measure has entered the fifth generation, and the pot...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): C04B35/48
Inventor 欧阳家虎刘占国周玉
Owner HARBIN INST OF TECH
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