Reparative coating and application thereof in repairing coating of silicon carbide-based composite material

A composite material and silicon carbide-based technology, which is applied in the field of repairing anti-oxidation coatings on the surface of silicon carbide-based composite materials, can solve problems such as poor chemical compatibility, low service temperature, and reduced coating reliability, and achieve high-temperature viscosity improvement. junction performance, improved reliability, and performance-enhancing effects

Active Publication Date: 2016-09-21
AEROSPACE RES INST OF MATERIAL & PROCESSING TECH +1
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

Among the common high-temperature binders, the inorganic binder has poor physical and chemical compatibility with the substrate, and the use temperature is low; while the h

Method used

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  • Reparative coating and application thereof in repairing coating of silicon carbide-based composite material
  • Reparative coating and application thereof in repairing coating of silicon carbide-based composite material

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0046] Weigh 15wt% polyborosilazane, 25wt% SiC powder, 25wt% ZrB 2 powder, 35wt% petroleum ether, wherein SiC powder particle size is 500nm, ZrB 2The particle size of the powder is 200nm. The above materials were placed in a ceramic ball mill jar and ball milled for 30 minutes to form a coating slurry. Grind the damaged part of the C / SiC composite coating, and form a buffer zone with a width of 5mm, wash and dry. Use a brush to brush the coating slurry on the surface of the composite material, wait for it to dry after each layer of brushing, and brush until it is flush with the surrounding coating. Adjust the temperature of the heat gun to 240°C and blow for 90 minutes to cure the coating. At this time, the damaged part of the C / SiC composite coating has been repaired.

Embodiment 2

[0048] Weigh 20wt% polysilazane, 20wt% SiC powder, 25wt% ZrB 2 powder, 5wt% B powder, 30wt% tetrahydrofuran, wherein SiC powder particle size is 500nm, ZrB 2 The particle size of the powder is 200nm, and the particle size of B powder is 500nm. The above materials were placed in a ceramic ball mill jar and ball milled for 10 minutes to form a coating slurry. The C / C-SiC composite was polished, washed with absolute ethanol, and dried. Use a brush to brush the coating slurry on the surface of the composite material to form an overall coating, wait for it to dry after each layer of brushing, and brush 8 times in total. Adjust the temperature of the heat gun to 300°C and blow for 60 minutes to cure the coating. At this time, the damaged part of the C / C-SiC composite coating has been repaired.

[0049] The surface micro-morphology of the obtained repaired coating is shown in Fig. figure 1 shown by figure 1 It can be seen that the surface of the repaired coating is smooth withou...

Embodiment 3

[0051] (1) Weigh 30wt% polycarbosilane-divinylbenzene solution, 35wt% SiC powder, and 35wt% tetrahydrofuran, wherein the particle size of SiC powder is 500nm. The above materials were placed in a ceramic ball mill jar and ball milled for 10 minutes to form a coating slurry. Grind the damaged part of the C / SiC composite coating, and form a buffer zone with a width of 5mm, wash and dry. Use a brush to apply the coating slurry to the damaged surface of the composite material and the buffer zone, wait for it to dry after each layer of brushing, and brush twice. Adjust the temperature of the heat gun to 180°C and blow for 30 minutes to cure the coating, and obtain a C / SiC composite material with a PCS-DVB-SiC coating on the damaged part.

[0052] (2) Weigh respectively 20wt% liquid polycarbosilane, 25wt% SiC powder, 15wt% ZrB 2 powder, 5wt% B powder and 35wt% n-hexane, wherein the particle size of SiC powder is 500nm, ZrB 2 The particle size of the powder is 200nm, and the parti...

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Abstract

The invention relates to a reparative coating and the application thereof in repairing the coating of a silicon carbide-based composite material, and belongs to the technical field of repairing the anti-oxidation coating on the surface of the silicon carbide-based composite material. The reparative coating is prepared through the brush-coating process, wherein a non-oxide ceramic precursor is adopted as an adhesive and ceramic powders are adopted as fillings. In a high-temperature service environment, the precursor inside the coating is pyrolyzed to generate ceramics. In this way, the oxidation resistance and the cohesive property of the coating are further improved. The ceramic precursor can be cured by using a hand-held heating device, so that the dependence on equipment is greatly reduced. Therefore, the reparative coating and the application thereof have a very important role in simply repairing the anti-oxidation coating on the surface of a heterogenic thermal structural component made of the silicon carbide-based composite material.

Description

technical field [0001] The invention relates to a repair coating and its application in the repair of silicon carbide-based composite material coatings, and belongs to the technical field of repair of oxidation-resistant coatings on the surface of silicon carbide-based composite materials. Background technique [0002] Silicon carbide-based composites have important application prospects in the aerospace field due to their low density, wear resistance, thermal shock resistance, and excellent high-temperature mechanical properties. In the field of hypersonic aircraft, experts at home and abroad proposed the design of "integration of thermal protection and structure", and prepared silicon carbide-based composite materials into large-scale special-shaped thermal structural components, which achieved remarkable results, showing that silicon carbide-based composite materials are used in large It has important application potential in areas of heat protection and load bearing. ...

Claims

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Application Information

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IPC IPC(8): C04B41/85C04B41/87C04B35/58C04B35/565
CPCC04B35/565C04B35/58C04B35/58078C04B41/009C04B41/5022C04B41/5059C04B41/85C04B41/87
Inventor 龚晓冬李军平赵彦伟张国兵胡继东冯志海
Owner AEROSPACE RES INST OF MATERIAL & PROCESSING TECH
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