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Multilayer-structure celsian environment barrier coating as well as application and preparation method thereof

A multi-layer structure and feldspar technology, which is applied in the field of multi-layer structure feldspar environmental barrier coating and its application and preparation, can solve the problems of thermal expansion coefficient mismatch, penetrating cracks, cracking and peeling, etc.

Pending Publication Date: 2021-05-18
XIAN XINGUI CERAMIC COMPOSITE MATERIAL CO LTD
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0005] The purpose of the present invention is to solve the problem of thermal expansion coefficient mismatch between layers of environmental barrier coating materials of silicon-based non-oxide ceramics existing in the prior art, which is easy to cause penetrating cracks, cracks and peeling phenomena, resulting in coating failure and matrix material oxidation. problem, but provides a multi-layer structure celsian environmental barrier coating and its use and preparation method

Method used

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Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0050] The multi-layer barite environmental barrier coating was prepared on the C / SiC substrate, and the specific steps were as follows:

[0051] 1) Prepare the bonding layer

[0052] Using the plasma spraying method, the silicon powder powder with a particle size of 300 mesh is sprayed on the base material to form a silicon layer;

[0053] When spraying, the total gas volume of plasma gas is 200lpm, of which N 2 accounted for 70%, H 2 The proportion is 20%, the proportion of Ar is 10%; the carrier gas flow rate is 7slpm; the spraying distance is 235mm; the powder feeding rate is 85g / min; when the silicon layer thickness reaches 90μm, stop spraying;

[0054] 2) Preparation of combined middle layer

[0055] 2.1) Using a plasma spraying method, the mullite powder with a powder particle size of 400 mesh is sprayed onto the silicon layer to form a mullite layer;

[0056] When spraying, the total gas volume of plasma gas is 150lpm, of which N 2 accounted for 70%, H 2 The prop...

Embodiment 2

[0064] The multi-layer barite environmental barrier coating is prepared on the SiC substrate, and the specific steps are as follows:

[0065] 1) Prepare the bonding layer

[0066] Using the plasma spraying method, the silicon powder powder with a powder particle size of 600 mesh is sprayed on the base material to form a silicon layer;

[0067] When spraying, the total gas volume of plasma gas is 150lpm, of which N 2 accounted for 60%, H 2 The proportion is 10%, the proportion of Ar is 30%; the carrier gas flow rate is 10slpm; the spraying distance is 200mm; the powder feeding rate is 45g / min; when the silicon layer thickness reaches 120μm, stop spraying;

[0068] 2) Preparation of combined middle layer

[0069] 2.1) Using a plasma spraying method, the mullite powder with a powder particle size of 200 mesh is sprayed onto the silicon layer to form a mullite layer;

[0070] When spraying, the total gas volume of plasma gas is 120lpm, of which N 2 accounted for 60%, H 2 The...

Embodiment 3

[0078] Preparation of multi-layer barite environmental barrier coating on SiC / SiC substrate, the specific steps are as follows:

[0079] 1) Prepare the bonding layer

[0080] Using the plasma spraying method, the silicon powder powder with a particle size of 400 mesh is sprayed on the base material to form a silicon layer;

[0081] When spraying, the total gas volume of plasma gas is 190lpm, of which N 2 accounted for 70%, H 2 The proportion is 10%, the proportion of Ar is 20%; the carrier gas flow rate is 5slpm; the spraying distance is 250mm; the powder feeding rate is 55g / min; when the thickness of the silicon layer reaches 100μm, stop spraying;

[0082] 2) Preparation of combined middle layer

[0083] 2.1) Using a plasma spraying method, the mullite powder with a powder particle size of 350 mesh is sprayed onto the silicon layer to form a mullite layer;

[0084] When spraying, the total gas volume of plasma gas is 120lpm, of which N 2 accounted for 65%, H 2 The propo...

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Abstract

The invention relates to a high-temperature-resistant and corrosion-resistant coating, in particular to a multilayer-structure celsian environment barrier coating as well as application and a preparation method thereof, and aims to solve the problems that in the prior art, interlayer thermal expansion coefficients of silicon-based non-oxide ceramic environment barrier coating materials are not matched, so that the phenomena of through cracks, cracking and peeling are easily caused, and the problems of coating failure and base material oxidation are solved. The coating comprises a bonding layer, a combined middle layer and a surface layer, the bonding layer is a silicon layer covering the surface of a base body, the combined middle layer comprises a mullite layer covering the silicon layer and a mullite and strontium-doped barium feldspar mixed layer covering the mullite layer, and the surface layer is a strontium-doped barium feldspar layer covering the mullite and strontium-doped barium feldspar mixed layer; the thickness of the bonding layer is 90-120 microns, the thickness of the combined middle layer is 90-140 microns, the thickness of the surface layer is 120-160 microns, and the total thickness of the coating is greater than or equal to 300 microns. A matrix material used by the coating is a SiC matrix, a C / SiC composite material matrix or a SiC / SiC composite material matrix.

Description

technical field [0001] The invention relates to a high-temperature-resistant and corrosion-resistant coating, in particular to a multilayer structure feldspar environmental barrier coating and its application and preparation method. Background technique [0002] With the development of aero-engines toward high thrust, high efficiency, and low fuel consumption, the environmental conditions in which aero-engines are used will become more stringent. In order to achieve a breakthrough in the high thrust-to-weight ratio and high efficiency of the aero-engine, the temperature of the gas in the engine must be increased, and the increase of the gas temperature will inevitably lead to an increase in the surface temperature of the hot-end parts of the high-pressure turbine. more severe test. [0003] In view of the fact that the hot end of an aero-engine is served in a high-temperature, water-oxygen corrosive environment, and needs to meet the characteristics of fatigue load and ultr...

Claims

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Application Information

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IPC IPC(8): C04B41/89
CPCC04B41/89C04B41/52C04B41/009
Inventor 张晰张紫琦刘典李建章成来飞
Owner XIAN XINGUI CERAMIC COMPOSITE MATERIAL CO LTD
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