Long-term high-temperature oxidation-resistant multi-element composite ceramic coating for carbon/carbon composite material and preparation and application methods thereof

A carbon composite material, high-temperature oxidation resistance technology, which is applied to carbon/carbon composite material long-term high-temperature oxidation-resistant multi-component composite ceramic coating, preparation and application fields, can solve problems such as easy cracking, and can meet the requirements of long-term use, Combines the effect of strong, superior thermal shock resistance

Active Publication Date: 2012-06-20
CENT SOUTH UNIV
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

[0004] The purpose of the present invention is to design and prepare a brand-new long-term high-temperature-resistant coating that is firmly bonded to the substrate and has no penetrating cracks for the situation that the ceramic coating on the surface of carbon / carbon composite materials is prone to defects such as cracks due to physical and chemical mismatches. Oxidized functional ceramic composite coating, and methods of preparation and application thereof

Method used

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  • Long-term high-temperature oxidation-resistant multi-element composite ceramic coating for carbon/carbon composite material and preparation and application methods thereof
  • Long-term high-temperature oxidation-resistant multi-element composite ceramic coating for carbon/carbon composite material and preparation and application methods thereof
  • Long-term high-temperature oxidation-resistant multi-element composite ceramic coating for carbon/carbon composite material and preparation and application methods thereof

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0035] First, cut the C / C composite material into a block sample of 20×20×5mm, grind the chamfer with 400# sandpaper, then finely grind it with 800# sandpaper, clean it with alcohol, and bake it at 120°C for 1-2 hours before use. ;

[0036] Next is the embedding process to prepare the SiC connection layer:

[0037] Si powder, SiC powder, C powder, Al 2 o 3 Powder is used as raw material to prepare mixed powder for embedding. The mass ratio of powder is: 50% Si-12% Al 2 o 3 -18%C-20%SiC. Weigh Si powder (over 325 mesh), Al 2 o 3 Powder (over 325 mesh), C powder (over 325 mesh), and SiC powder (over 325 mesh) use ethanol as a dispersant, put them in a planetary ball mill and mix well, take them out and dry them before use. Finally, put the C / C composite material in a graphite crucible and bury it completely with the mixed powder, then put the crucible into a high-temperature furnace, from room temperature to 1100°C, it takes 50min; from 1100°C to 1800°C, it takes 50min ...

Embodiment 2

[0044] Using 70%Si-4%Al 2 o 3 -12%C-14%SiC embedding material to prepare SiC connection layer, the parameters used are: H 2 / MTS=10 (molar ratio), Ar flow rate is 200ml min -1 , the deposition pressure is 2 The powder (YSZ) is prepared according to the powder ratio of 60:30:10 to prepare the ceramic outer coating, and the rest of the steps are the same as above. After 150h, 1500°C air oxidation resistance test of the prepared coating sample, the coating remains intact without falling off, the oxidation weight gain rate is 0.35%, and the coating sample strength retention rate is 96.8%.

Embodiment 3

[0046] Using 45%Si-10%Al 2 o 3 -10%C-35%SiC embedding material to prepare SiC connection layer, the parameters used are: H 2 / MTS=12 (molar ratio), Ar flow rate is 180ml min -1 , deposition pressure 2 The powder (YSZ) is prepared according to the powder ratio of 75:25:5 to prepare the ceramic outer coating, and the rest of the steps are the same as above. The prepared coating sample was subjected to the oxidation resistance test in air at 1500°C for 150 hours. The coating remained intact and did not fall off. The oxidation weight gain rate was 0.11%, and the strength retention rate of the coating sample was 95.7%.

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Abstract

The invention provides a long-term high-temperature oxidation-resistant multi-element composite ceramic coating for a carbon/carbon composite material and preparation and application methods thereof. The long-term high-temperature oxidation-resistant multi-element composite ceramic coating is a composite coating on the surface of the carbon/carbon composite material and sequentially (from inside to outside) comprises a SiC connection layer prepared with an embedding method, a SiC sealing layer prepared with a chemical vapor deposition method and a SiO2-Y2Si2O7-ZrSiO4-Al2SiO5 ceramic layer prepared with a brush coating method and an in-situ oxidation reaction method, wherein the SiC connection layer is combined with a matrix and exerts the function of connecting the matrix, the SiC sealinglayer exerts the function of filling defects of an inner layer, and the outermost SiO2-Y2Si2O7-ZrSiO4-Al2SiO5 ceramic layer serves as an oxygen blocking layer and exerts the function of self-healing and oxygen blocking. The long-term high-temperature oxidation-resistant multi-element composite ceramic coating has the advantages of firmness in combination with the matrix, no run-through crack, long-term high-temperature oxidation resistance, and capability of being completely applied to the preparation of non-direct-ablation heat-resistant structural members around the head and of the wings ofa hypersonic aircraft and the preparation of a material for the tailpipe chamber of an aircraft engine.

Description

technical field [0001] The invention relates to the surface treatment of a carbon / carbon composite material, in particular to a carbon / carbon composite material used for indirect ablation heat-resistant structural parts around the head and wings of a hypersonic aircraft and a new type of aero-engine afterburner A long-time high-temperature oxidation-resistant multi-layer multi-component composite ceramic coating on the surface of a carbon / carbon composite material for a traditional superalloy material and its preparation and application method. Background technique [0002] Carbon / carbon composite material is a new type of high-temperature material with carbon fiber reinforced carbon matrix, which was accidentally discovered in 1958 by Chance-Vought Aviation in the United States. Carbon / carbon composite materials are entirely composed of a single carbon material, with high modulus, low density, small thermal expansion coefficient, ablation resistance, fatigue resistance, che...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): C04B41/89
Inventor 熊翔曾毅张武装殷玲郭顺
Owner CENT SOUTH UNIV
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