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Anti-ablation composite coating and preparation method thereof

A composite coating and anti-ablation technology, which is applied in the direction of coating, metal material coating process, fusion spraying, etc., can solve the complex molding process, high sintering temperature, and the difficulty in preparing and processing large high-temperature ablation-resistant structural parts, etc. problems, to achieve the effect of low preparation cost, high mechanical properties, and good anti-ablation effect

Inactive Publication Date: 2015-03-04
XIAN TECHNOLOGICAL UNIV
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0006] However, the complexity of the molding process and the high sintering temperature make the preparation and processing of irregularly shaped large high-temperature ablation-resistant structural parts more difficult.

Method used

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  • Anti-ablation composite coating and preparation method thereof
  • Anti-ablation composite coating and preparation method thereof

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0025] A kind of preparation method of anti-ablation composite coating of the present invention, comprises the following steps:

[0026] [1.1] Preparation of composite powder for spraying: Weigh ZrB with a mass ratio of 40.36:44.64:5.31:9.7 2 , ZrC, SiC, ZrO 2 Powder, the designed volume ratio is 40:40:10:10. ZrB 2 , The median particle size of ZrC powder is 10μm, SiC, ZrO 2 The median particle size of the powder was 1 μm. Mixing is carried out through a ball mill, specific parameters: ball-to-material ratio 10:1, ball mill speed 120 rpm, and mixing time 3 hours to ensure sufficient and uniform mixing.

[0027] [1.2] Preparation of substrate bonding layer: Incol718 superalloy was used as the substrate, and the substrate was sandblasted before the bonding layer was prepared. The Amdry997 NiCoCrAlYTa produced by Sulzer Metco was selected as the bonding layer material, and the bonding layer was prepared by cold spraying. The accelerating gas during spraying was He gas, the t...

Embodiment 2

[0032] A preparation method of the anti-ablation composite coating on the surface of boiler steel of the present invention comprises the following steps:

[0033] [2.1] Preparation of composite powder for spraying: Weigh ZrB with a mass ratio of 40.96:45.5:7.18:6.56 2 , ZrC, SiC, ZrO 2 Powder, the designed volume ratio is 40:40:13.33:6.67. ZrB 2 , The median particle size of ZrC powder is 10μm, SiC, ZrO 2 The median particle size of the powder was 1 μm. Mixing is carried out through a ball mill, specific parameters: ball-to-material ratio 10:1, ball mill speed 120 rpm, and mixing time 3 hours to ensure sufficient and uniform mixing.

[0034] [2.2] Preparation of substrate bonding layer: 20G boiler steel is used as the substrate, and the substrate is sandblasted before preparing the bonding layer. The Amdry9951 type CoNiCrAlY produced by Sulzer Metco was selected as the bonding layer material, and the bonding layer was prepared by cold spraying. The accelerating gas during...

Embodiment 3

[0037] A method for preparing an anti-ablation composite coating on an aluminum alloy surface according to the present invention, comprising the following steps:

[0038] [3.1] Preparation of composite powder for spraying: Weigh ZrB with a mass ratio of 54.58:30.19:5.38:9.84 2 , ZrC, SiC, ZrO 2 Powder, the designed volume ratio is 53.33:26.67:10:10. ZrB 2 , The median particle size of ZrC powder is 10μm, SiC, ZrO 2 The median particle size of the powder was 1 μm. Mixing is carried out through a ball mill, specific parameters: ball-to-material ratio 10:1, ball mill speed 120 rpm, and mixing time 3 hours to ensure sufficient and uniform mixing.

[0039] [3.2] Preparation of substrate bonding layer: ZL109 piston alloy is used as the substrate, and the substrate is sandblasted before preparing the bonding layer. The Amdry960 NiCrAl produced by Sulzer Metco was selected as the bonding layer material, and the bonding layer was prepared by cold spraying. The accelerating gas dur...

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Abstract

The invention discloses an anti-ablation composite coating and a preparation method thereof. The anti-ablation composite coating consists of a bonding layer and a composite ceramic anti-ablation layer, wherein the composite ceramic anti-ablation layer is manufactured by plasma spray deposition of ZrB2-ZrC-SiC-ZrO2 composite ceramic; during preparation, B2O5Si products formed on ceramic ZrB2, ZrC, and SiC particle interfaces facilitate the connection and reinforcement of the interfaces. According to the anti-ablation composite coating and the preparation method thereof, the composite ceramic does not need to be sintered; the limit on the product shape during sintering is overcome; the requirements of resisting high-temperature ablation during preparation of large-sized structural components are met.

Description

technical field [0001] The invention relates to the technical fields of aerospace, metallurgy, machinery, material processing, etc., and relates to a high-temperature ablation-resistant composite coating and a preparation method thereof. Background technique [0002] The aerospace field has extremely high requirements on the high temperature resistance and ablation resistance of materials. Aerospace engines, gas turbines, internal combustion engines, boilers and other combustion chamber heating components also have similar high-temperature ablation phenomena, and also need protection against high-temperature ablation. New materials that can maintain physical and chemical stability for a long time in high-temperature, ultra-high-temperature gas and oxidizing atmospheres have become a research hotspot. The materials that can meet the ultra-high temperature ablation of spacecraft are mainly multi-component composite ceramics composed of borides and carbides. Such materials are...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): C23C4/10C23C4/08C23C4/02C23C4/12C23C4/073C23C4/126C23C4/129C23C4/134
CPCC23C4/10
Inventor 高培虎李建平杨忠郭永春夏峰段洪波
Owner XIAN TECHNOLOGICAL UNIV