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Multiple-oxides codoped molten glass corrosion-resistant thermal barrier coating layer

A technology of thermal barrier coating and polyoxide, which is applied in coating, fusion spraying, metal material coating process, etc., can solve the problems of high cost and coating failure, reduce porosity, improve phase stability, Effect of Improving CMAS Corrosion Resistance

Active Publication Date: 2018-12-04
DALIAN POLYTECHNIC UNIVERSITY
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

The way of post-treatment undoubtedly adds a protective layer on the surface of YSZ, which can effectively prevent the infiltration of CMAS and greatly improve the corrosion resistance of the coating against CMAS. However, the failure of the thermal barrier coating is the result of thermal coupling. The infiltration of CMAS is prevented, but TGO will still grow with the increase of service time, and the stress concentration at the interface will still lead to coating failure, and the cost is high

Method used

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  • Multiple-oxides codoped molten glass corrosion-resistant thermal barrier coating layer
  • Multiple-oxides codoped molten glass corrosion-resistant thermal barrier coating layer
  • Multiple-oxides codoped molten glass corrosion-resistant thermal barrier coating layer

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0045] according to figure 1 The flow chart shown prepares the ceramic layer of the polyoxide co-doped thermal barrier coating of the present invention:

[0046] According to mass percentage, Y 2 o 3 6.8%, ZrO 2 73%, Al 2 o 3 16.9%, TiO 2 3.3%; the specific steps are as follows:

[0047] Step 1. Powder mixing: Weigh the ingredients according to the formula designed in step 1, grind them thoroughly with an agate mortar, and mix evenly to obtain a uniformly mixed mixed powder 1;

[0048] Step 2. Spray granulation: use the mixed powder 1 uniformly mixed in step 1 to obtain the powder 2 for plasma spraying with a particle size between 20-40 μm by spray granulation;

[0049] Step 3. Spraying: The temperature at the center of the plasma arc is 2 x 10 4 In the case of K and He protection, the powder 2 prepared in step 2 is plasma sprayed at a spraying speed of 1 Mach, so that the powder 2 is deposited on the surface of the bonding layer NiCrAlY, and the layers are stacked...

Embodiment 2

[0052] according to figure 1 The flow chart shown prepares the ceramic layer of the polyoxide co-doped thermal barrier coating of the present invention:

[0053] According to mass percentage, Y 2 o 3 5.1%, ZrO 2 59.1%, Al 2 o 3 13.0%, TiO 2 3.25%; Nd 2 o 3 9.0%; Yb 2 o 3 10.55%; the specific steps are as follows:

[0054] Step 1. Powder mixing: Weigh the ingredients according to the formula designed in step 1, grind them thoroughly with an agate mortar, and mix evenly to obtain a uniformly mixed mixed powder 1;

[0055] Step 2. Spray granulation: use the mixed powder 1 uniformly mixed in step 1 to obtain the powder 2 for plasma spraying with a particle size between 20-40 μm by spray granulation;

[0056] Step 3. Spraying: The temperature at the center of the plasma arc is 2 x 10 4 In the case of K and He protection, the powder 2 prepared in step 2 is plasma sprayed at a spraying speed of 1 Mach, so that the powder 2 is deposited on the surface of the bonding l...

Embodiment 3

[0059] according to figure 1 The flow chart shown prepares the polyoxide co-doped thermal barrier coating of the present invention:

[0060] According to mass percentage, Y 2 o 3 6.0%, ZrO 2 65.0%, Al 2 o 3 13.0%, TiO 2 3.3%; Nd 2 o 3 5.0%; Yb 2 o 3 7.7%; the specific steps are as follows:

[0061] Step 1. Powder mixing: Weigh the ingredients according to the formula designed in step 1, grind them thoroughly with an agate mortar, and mix evenly to obtain a uniformly mixed mixed powder 1;

[0062] Step 2. Spray granulation: use the mixed powder 1 uniformly mixed in step 1 to obtain the powder 2 for plasma spraying with a particle size between 20-40 μm by spray granulation;

[0063] Step 3. Spraying: The temperature at the center of the plasma arc is 2 x 10 4 In the case of K and He protection, the powder 2 prepared in step 2 is plasma sprayed at a spraying speed of 1 Mach, so that the powder 2 is deposited on the surface of the bonding layer NiCrAlY, and the la...

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Abstract

The invention discloses a molten glass corrosion-resistant thermal barrier coating layer. The molten glass corrosion-resistant thermal barrier coating layer comprise a bonding layer NiCrAlY and a ceramic layer; and the ceramic layer comprises, by mass, 0-10.54% of Yb2O3, 5.1-6.8% of Y2O3, 59.1-73% of ZrO2, 13-16.9% of Al2O3, 3.25-3.3% of TiO2, 0-9% of Nd2O3 and 0-10.54% of Yb2O3. The invention also provides a preparation method of the ceramic layer of the plasma sprayed thermal barrier coating layer. The method comprises the following steps: powder preparation, mixing, granulation and spraying. The thermal barrier coating layer obtained by using the above technical scheme has a significantly better molten glass corrosion resistance than conventional thermal barrier coating layers. The method is simple to operate; and compared with other methods, the method in the invention has the advantages of low cost, no additional device, and very broad application prospect in the field of aeroengines with molten glass corrosion resistance.

Description

technical field [0001] The invention relates to a formula of a thermal barrier coating and a preparation process thereof, in particular to a polyoxide co-doped thermal barrier coating resistant to corrosion of molten glass. Background technique [0002] Thermal barrier coatings (TBCs) are protective coatings that can insulate heat and prevent parts from being oxidized and corroded in high temperature environments. Its heat insulation function can reduce the actual working temperature of the base metal under the coating, which can effectively improve the service life of the parts. TBCs are mainly used on the surface of metal parts working at high temperature, such as the surface of aircraft turbine blades, hot end parts of weaponry propulsion system and steam turbine combustion chamber parts. In recent years, research on thermal barrier coatings has mainly focused on thermal shock resistance and high temperature oxidation resistance. Most of the test conditions are that the ...

Claims

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Application Information

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IPC IPC(8): C23C4/11C23C4/134C23C4/073
CPCC23C4/073C23C4/11C23C4/134
Inventor 张晶晶韩圣辉张昊王知行白岩李逸王志强林海
Owner DALIAN POLYTECHNIC UNIVERSITY
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