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In-situ synthesis method for preparing composite thermal barrier coating

A thermal barrier coating, in-situ synthesis technology, applied in coatings, metal material coating processes, air transportation, etc., can solve the problem of reducing the thermal conductivity of materials, reducing the mean free path of phonons, and increasing the phonons of ceramic layers. Scattering and other problems, to extend service life, improve thermal stability and anti-oxidation performance, and achieve good matching results

Inactive Publication Date: 2013-02-13
XI AN JIAOTONG UNIV
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

This kind of ceramic layer has more vacancies and a more complex unit cell structure than YSZ, and the rare earth atomic mass will increase the scattering of phonons in the ceramic layer and reduce the mean free path of phonons, thereby reducing the Thermal conductivity

Method used

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  • In-situ synthesis method for preparing composite thermal barrier coating

Examples

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Comparison scheme
Effect test

Embodiment 1

[0027] The bonding layer in the workpiece thermal barrier coating is NiCrAlY coating, in which the mass fractions of Ni, Cr, Al and Y are 69%, 20%, 10% and 1%, respectively, and the thickness is 100 μm. After surface treatment, La 2 Zr 2 o 7 The preparation method of the / YSZ composite ceramic layer is realized according to the following steps:

[0028] a the La with a molar ratio of 1:2 2 o 3 and ZrO 2 Powder mixing and ball milling for 48 hours;

[0029] b ball milled La 2 o 3 / ZrO 2 The mixed powder and YSZ powder are mixed at a molar ratio of 1:2;

[0030] c. Spray the mixed powder obtained in step b on the surface of the bonding layer by plasma spraying method, and the thickness of the ceramic coating is 300 μm. Spraying parameters: voltage 74V, current 650A, powder feeding rate 60g min -1 , argon flow rate 2550L h -1 , hydrogen flow rate 425L h -1 , the spraying distance is 120mm;

[0031] d Place the sprayed thermal barrier coating ceramic layer in a resis...

Embodiment 2

[0033] The bonding layer in the workpiece thermal barrier coating is NiCrAlY coating, in which the mass fractions of Ni, Cr, Al and Y are 69%, 20%, 10% and 1%, respectively, and the thickness is 80 μm. After surface treatment, Nd 2 Zr 2 o 7 / YSZ conforms to the preparation method of the ceramic layer according to the following steps:

[0034] a Add Nd with a molar ratio of 1:2 2 o 3 and ZrO 2 Powder mixing and ball milling for 72 hours;

[0035] b ball milled Nd 2 o 3 / ZrO 2 The mixed powder and YSZ powder are mixed at a molar ratio of 1:4;

[0036] c. Spray the mixed powder obtained in step b on the surface of the bonding layer by plasma spraying method, and the thickness of the ceramic coating is 200 μm. Spraying parameters: voltage 74V, current 650A, powder feeding rate 60g min-1 , argon flow rate 2550L h -1 , hydrogen flow rate 425L h -1 , the spraying distance is 100mm;

[0037] d Place the sprayed thermal barrier coating ceramic layer in a resistance furnace...

Embodiment 3

[0039] The bonding layer in the workpiece thermal barrier coating is NiCrAlY coating, in which the mass fractions of Ni, Cr, Al and Y are 69%, 20%, 10% and 1%, respectively, and the thickness is 120 μm. After surface treatment, Sm 2 Zr 2 o 7 The preparation method of the / YSZ composite ceramic layer is realized according to the following steps:

[0040] a Sm with a molar ratio of 1:2 2 o 3 and ZrO 2 Powder mixing and ball milling for 18 hours;

[0041] b Sm after ball milling 2 o 3 / ZrO 2 The mixed powder and YSZ powder are mixed in a molar ratio of 4:1;

[0042] c. Spray the mixed powder obtained in step b on the surface of the bonding layer by plasma spraying method, and the thickness of the ceramic coating is 400 μm. Spraying parameters: voltage 74V, current 650A, powder feeding rate 60g min -1 , argon flow rate 2550L h -1 , hydrogen flow rate 425L h -1 , the spraying distance is 150mm;

[0043] d Place the sprayed thermal barrier coating ceramic layer in a re...

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Abstract

The invention discloses an in-situ synthesis method for preparing a composite thermal barrier coating, which comprises the following steps: mixing R2O3 / ZrO2 mixed powder, which is obtained by mixing R2O3 powder and ZrO2 powder and carrying out ball milling, with YSZ powder; and spraying a bonding layer surface on a high-temperature alloy matrix by a plasma spraying method, putting in a resistance furnace, and sintering at 1000-1400 DEG C under air conditions to prepare the R2Zr2O7-dispersed YSZ ceramic layer. The method eliminates the interface between the R2Zr2O7 rare-earth zirconate ceramic layer and the YSZ ceramic layer, so that the thermal barrier coating has high-temperature phase stability, has lower heat conductivity than the traditional YSZ, and lowers the oxygen permeability of the ceramic layer; and compared with the simple rare-earth zirconate ceramic layer, the composite thermal barrier coating has longer service life, and can satisfy the requirements for hot-end component long-term service, high-temperature oxidation resistance and the like.

Description

【Technical field】 [0001] The invention relates to the field of thermal barrier coatings, in particular to a method for preparing thermal barrier coating ceramic layers used for high-temperature parts of gas turbine engines. 【Background technique】 [0002] Gas turbine engines are widely used in aircraft, ships, vehicles and generator sets. In the past 50 years, the temperature before the turbine of a typical gas turbine has increased from 960°C to 1500-1600°C, and the turbine blades are mostly composed of Ni-based (or Co-based) superalloys, and this temperature has slowly approached its melting point. Prepare a layer of ceramic material on the surface of the blade to prevent direct contact between the high-temperature flame and the substrate, so as to achieve the purpose of increasing the operating temperature and reducing the cooling requirements of the system. This part of the coating system that plays a role in heat insulation and oxidation resistance is the so-called the...

Claims

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Application Information

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IPC IPC(8): C23C4/10C23C4/12C23C4/11C23C4/134
CPCY02T50/60
Inventor 梁工英祝超丁秉钧王铁军虞烈
Owner XI AN JIAOTONG UNIV
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