Method for preparing zirconium carbide ceramic boundary phase on surface of carbon fiber

A zirconium carbide and carbon fiber technology, applied in the directions of carbon fiber, chemical instruments and methods, carbon compounds, etc., can solve the problems of high preparation cost, difficult control, complicated process, etc., and achieve the effect of uniform interface layer thickness and good ablation resistance.

Active Publication Date: 2014-05-21
嘉兴睿创新材料有限公司
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

However, C f Ultra-high temperature modification of / SiC composite materials is a new research direction, and there are few public reports on the interface phase of ultra-high temperature ceramics
From a theoretical analysis, chemical vapor deposition is a feasible process for preparing the interface phase of ultra-high temperature ceramics, but the process is complicated, difficult to control, and the preparation cost is high

Method used

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  • Method for preparing zirconium carbide ceramic boundary phase on surface of carbon fiber
  • Method for preparing zirconium carbide ceramic boundary phase on surface of carbon fiber

Examples

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Effect test

Embodiment 1

[0024] Weigh 24g of phenolic resin, dissolve it in a mixed solvent of 72g alcohol and butanone to prepare a solution, add 2.28g triolein dropwise, weigh 91.22g of Zr powder, mix it with the above solution for 24 hours by ball milling, and prepare a stable Suspension: put the preform with a fiber content of 26vol% in the suspension, vacuum impregnate for 2 hours, take it out and dry it in vacuum at 80°C for 3 hours; repeat the vacuum impregnation-drying process for 3 times, and place the preform Place it in a graphite crucible and move it to a vacuum carbon tube furnace. Under the condition that the initial vacuum degree in the furnace is 85mtorr, heat it to 1000°C and keep it for 15 minutes to form a ZrC interface phase on the surface of the fiber. The SEM photo of the ZrC interfacial phase prepared by the present embodiment, as figure 1 Shown: the thickness of the interface phase is 70nm (the white ring on the surface of the fiber shown by the arrow in the figure), and the th...

Embodiment 2

[0026] The difference between this example and Example 1 is only that the mass of triolein is 2.01 g, and the mass of Zr powder is 80.27 g.

[0027] The rest of the content is exactly the same as described in Example 1.

[0028] Through detection and analysis, it is found that the thickness of the ZrC interface phase prepared in this example is about 57nm, and the 3D ceramic matrix composite material prepared with the fiber prefabricated body as a reinforcement is evaluated by a plasma wind tunnel experiment with a temperature as high as 2250K. The erosion rate is 0.0023g / s.

Embodiment 3

[0030] The difference between this example and Example 1 is only that the mass of triolein added dropwise is 2.33 g, and the mass of Zr powder is 93.04 g.

[0031] The rest of the content is exactly the same as described in Example 1.

[0032] Through detection and analysis, it is known that the thickness of the ZrC interface phase prepared in this example is about 85nm, and the 3D ceramic matrix composite material prepared with the fiber prefabricated body as a reinforcement is evaluated by a plasma wind tunnel experiment with a temperature as high as 2250K. The erosion rate is 0.0015g / s.

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Abstract

The invention discloses a method for preparing a zirconium carbide ceramic boundary phase on the surface of a carbon fiber. The method comprises the following steps: dissolving a phenolic resin into an organic solvent, adding a dispersing agent and zirconium powder, ball-milling to form stable suspension, putting carbon fiber preform into the prepared suspension for vacuum dipping-drying treatment for multiple times so as to prepare preform, putting the prepared preform into a vacuum carbon tube furnace for thermal treatment, and performing in-situ reaction at 900-1,200 DEG C and with the vacuum degree of 50-100 millitorrs, thereby obtaining the zirconium carbide ceramic boundary phase. By adopting the method, the ZrC super high temperature ceramic boundary phase with the thickness of 50nm-100nm can be achieved on the surface of the carbon fiber through in-situ reaction, the boundary layer is uniform in thickness, easy to control and free of defects such as cracks, and the carbon fiber preform obtained by the method disclosed by the invention is a 3D ceramic-based composite material prepared from a reinforcing body, and has good anti-ablation capability.

Description

technical field [0001] The invention relates to a method for preparing an interface phase of zirconium carbide ceramics on the surface of carbon fibers, specifically, a method for preparing an interface phase of zirconium carbide ceramics on the surface of carbon fibers based on an in-situ reaction, and belongs to the technical field of composite materials. Background technique [0002] When a hypersonic spacecraft re-enters the atmosphere, the nose cone and the leading edge of the wing must withstand the harsh thermal environment of ultra-high temperature (2000-3000°C) and large heat flow. The throat lining part of the hot end part of the engine needs to withstand complex thermal stress environment, high temperature of 2000-3000 ℃ and high-speed particle erosion, which puts forward strict requirements on materials, such as high melting point, good anti-oxidation and thermal shock resistance, low Coefficient of thermal expansion, low vapor pressure (especially at high temper...

Claims

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Application Information

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IPC IPC(8): D06M11/74C01B31/30D06M101/40C01B32/914
Inventor 董绍明阚艳梅章良润王震
Owner 嘉兴睿创新材料有限公司
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