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Ablation-resistant material preparation method

An ablation-resistant, prefabricated technology, applied in the field of engineering materials, can solve problems such as low bonding strength, and achieve the effects of low cost, controllable process and simple preparation process

Inactive Publication Date: 2018-08-24
XIAN AVIATION BRAKE TECH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

Hafnium carbide modified C / C composites prepared by CVD process, although the HfC coating has better uniformity and structure is easy to control, but because the combination between the substrate and the coating belongs to physical adsorption, the bonding strength between the two is low

Method used

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Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0020] Carbon fiber needle felt prefabricated body is used. Using propylene as the carbon source gas, a chemical vapor deposition process is used to deposit a pyrolytic carbon layer on the surface of the carbon fiber of the preform. The specific conditions are as follows: the deposition temperature is 1020-1030°C, the pressure is 3-5KPa, the propylene flow rate is 4-6L / min, the deposition time is 40-50h, and the density of the sample after deposition is 0.8g / cm 3 . Put the carbon fiber prefabricated body deposited with the carbon interface layer into the vacuum impregnation device, slowly add the HfC ceramic phase precursor impregnation solution, control the vacuum degree below 0.5KPa, and the impregnation time is between 60-90min. Transfer the impregnated sample to an oven, adjust the oven temperature to 180-200°C, dry for 8-10 hours, and put the cross-linked and cured sample into a heat treatment furnace, and adjust the heating rate to 5-10 hours. 8°C / min, the temperature ...

Embodiment 2

[0022] Carbon fiber needle felt prefabricated body is used. Using propylene as the carbon source gas, a chemical vapor deposition process is used to deposit a pyrolytic carbon layer on the surface of the carbon fiber of the preform. The specific conditions are as follows: the deposition temperature is 1020-1030°C, the pressure is 3-5KPa, the propylene flow rate is 4-6L / min, the deposition time is 80-90h, and the density of the sample after deposition is 1.0g / cm 3 . Put the carbon fiber prefabricated body deposited with the carbon interface layer into the vacuum impregnation device, slowly add the HfC ceramic phase precursor impregnation solution, control the vacuum degree below 0.5KPa, and the impregnation time is between 60-90min. Transfer the impregnated sample to an oven, adjust the oven temperature to 180-200°C, dry for 8-10 hours, and put the cross-linked and cured sample into a heat treatment furnace, and adjust the heating rate to 5-10 hours. 8°C / min, the temperature ...

Embodiment 3

[0024] Carbon fiber needle felt prefabricated body is used. Using propylene as the carbon source gas, a chemical vapor deposition process is used to deposit a pyrolytic carbon layer on the surface of the carbon fiber of the preform. The specific conditions are as follows: the deposition temperature is 1020-1030°C, the pressure is 3-5KPa, the propylene flow rate is 4-6L / min, the deposition time is 130-140h, and the density of the sample after deposition is 1.2g / cm 3 . Put the carbon fiber prefabricated body deposited with the carbon interface layer into the vacuum impregnation device, slowly add the HfC ceramic phase precursor impregnation solution, control the vacuum degree below 0.5KPa, and the impregnation time is between 60-90min. Transfer the impregnated sample to an oven, adjust the oven temperature to 180-200°C, dry for 8-10 hours, and put the cross-linked and cured sample into a heat treatment furnace, and adjust the heating rate to 5-10 hours. 8°C / min, the temperatur...

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Abstract

The invention relates to an ablation-resistant material preparation method which includes the steps: 1) preparing a carbon fiber prefabricated body by a three-dimensional needling weaving method, anddepositing a carbon interface layer on carbon fiber surface of the carbon fiber prefabricated body to form a carbon billet; 2) leading a ceramic phase into the carbon billet, filling inner space of the carbon billet with the ceramic phase. The carbon interface layer is provided with pyrolytic carbon formed on the carbon fiber surface by a chemical vapor deposition process, the ceramic phase is anHfC ceramic, and the carbon billet is soaked into HfC ceramic precursor solution and cross-linked, cured, pyrolyzed and treated at high temperature to obtain the ceramic phase. According to the method, a preparation technology is simple, controllable in process and relatively low in cost, and the quality and the line ablation rate of a sample is 1.64 milligrams / second and 2.77 micrometers / second when a prepared ablation-resistant material is ablated for 120 seconds at the temperature of 2500 DEG C.

Description

technical field [0001] The invention belongs to the technical field of engineering materials and relates to a preparation method of an ablation-resistant material. Background technique [0002] Carbon-carbon composites have low density, high thermal conductivity, excellent thermal shock resistance and good ablation resistance, and are ideal materials for preparing high-temperature hot-end structural components. They have been widely used in recent years Aeronautics and aerospace fields. However, in the environment of high temperature and high pressure gas flow, carbon-carbon composite materials will rapidly oxidize and ablate, which limits its application. In order to improve the application efficiency of carbon-carbon composite materials in high-temperature environments, an important way to improve the ablation resistance performance proposed in recent years is to introduce refractory metal carbides (ZrC, HfC) to improve the oxidation resistance of carbon-carbon composite ...

Claims

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Application Information

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IPC IPC(8): C04B35/56C04B35/80C04B35/622C04B35/628
CPCC04B35/806C04B35/5622C04B35/622C04B35/62873C04B35/62884C04B2235/48C04B2235/616C04B2235/6562C04B2235/6567C04B2235/658C04B2235/77
Inventor 薛亮周蕊杜淑娣施伟伟邢少敏
Owner XIAN AVIATION BRAKE TECH
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