Low-temperature preparation method of C/SiC ceramic matrix composite material

A composite material and ceramic-based technology, which is applied in the field of preparation of inorganic non-metallic materials, can solve the problems of inability to obtain performance composite materials, poor mechanical properties of composite materials, uneconomical material properties, etc., and achieves short preparation period and excellent mechanical properties. , the effect of simple structure

Inactive Publication Date: 2008-07-23
NAT UNIV OF DEFENSE TECH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, simply lowering the preparation temperature cannot obtain composite materials with excellent properties.
For example, simply transplanting the PIP process and reducing the preparation temperature of the composite material to 800-1000°C, the mechanical properties of the obtained composite material are very poor (such as the bending strength is less than 100MPa, which cannot meet the requirements of engineering applications)
Using CVI / CVD process, lowering the deposition / infiltration temperature to 800-1000°C, the infiltration rate will be greatly reduced, and the preparation cycle may be extended from the original 2-3 months to 6-12 months, while the fiber is at high temperature for a long time , is also susceptible to more serious damage, not only uneconomical but also poor in material properties

Method used

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Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0016] A low-temperature preparation method of a three-dimensional C / SiC ceramic matrix (3D-C / SiC) composite material, comprising the following steps:

[0017] 1. Carbon fiber pretreatment: put the carbon fiber prefabricated part (three-dimensional five-way weaving, fiber volume fraction 53.1%) in a high-temperature vacuum furnace, and start heating after vacuuming until the vacuum degree is lower than 30Pa. The heating rate is 20°C / min. Keep warm for 1 hour after reaching 1600°C, cool down naturally, and pass inert gas during the cooling process;

[0018] 2. Vacuum impregnation: Prepare PCS and xylene in a mass ratio of 1:1 to make a uniform precursor solution, put the pretreated carbon fiber preform into the impregnation tank, first evacuate until the vacuum degree is lower than 100Pa, and then turn off the vacuum pump Add the PCS / xylene precursor solution, keep it for 2 hours, then take it out and let it dry naturally for 10 hours;

[0019] 3. High-temperature cracking: Cr...

Embodiment 2

[0030] A low-temperature preparation method of a three-dimensional C / SiC ceramic matrix (3D-C / SiC) composite material, comprising the following steps:

[0031] 1. Carbon fiber pretreatment: put the carbon fiber prefabricated part (three-dimensional five-way weaving, fiber volume fraction 53.1%) in a high-temperature vacuum furnace, and start heating after vacuuming until the vacuum degree is lower than 30Pa. The heating rate is 20°C / min. After reaching 1200°C, keep warm for 2 hours, cool down naturally, and pass inert gas during the cooling process;

[0032] 2, this step is the same as step 2 of embodiment 1;

[0033] 3. High-temperature cracking: crack the above-mentioned dried carbon fiber preform in a cracking furnace, raise the temperature to 1000°C at a heating rate of 10°C / min under the protection of nitrogen, keep it for 1 hour, and cool down naturally under the protection of nitrogen;

[0034] 4. Densification: Repeat the vacuum impregnation-high temperature pyrolysis...

Embodiment 3

[0037] A low-temperature preparation method of a two-dimensional C / SiC ceramic matrix (2D-C / SiC) composite material, comprising the following steps:

[0038] 1. Carbon fiber pretreatment: put the carbon fiber cloth laminated prefabricated part (fiber volume fraction 47.1%) in a high-temperature vacuum furnace, and start heating after vacuuming until the vacuum degree is lower than 30Pa. The heating rate is 20°C / min, and the temperature is raised to 1200 After holding for 2 hours at ℃, cool down naturally, and pass inert gas during the cooling process;

[0039] 2, this step is the same as step 2 of embodiment 1;

[0040] 3, this step is the same as step 3 of embodiment 1;

[0041] 4. This step is the same as Step 4 in Example 2.

[0042] The density of the two-dimensional C / SiC ceramic matrix composite prepared by the above method is 1.76g / cm 3 , the bending strength is 329.61MPa, and the fracture toughness is 15.65MPa m 1 / 2 .

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Abstract

The invention discloses a low-temperature preparation method for a C / SiC ceramic composite, which is characterized in that: with ceramic properties of the precursor of the organic polymer under low temperature, carbon fibers are adopted as reinforcing materials and infiltration pyrolysis is adopted for the precursor; processing steps, such as the carbon fibers pre-treatment, vacuum infuse, high-temperature pyrolysis, and densification, are applied to prepare C / SiC ceramic composites with excellent mechanical properties under low temperature. Compared with the traditional preparation method for ceramic composites, the low-temperature preparation method has the advantages of reducing preparation temperature, simplifying processing facilities, reducing cost, and shortening preparation cycle.

Description

technical field [0001] The invention relates to a preparation process of an inorganic non-metallic material, in particular to a preparation method of a C / SiC ceramic matrix composite material. Background technique [0002] C / SiC ceramic matrix composite material came into being with the development of modern science and technology, and it is a new type of material developed after carbon-carbon composite material. C / SiC ceramic matrix composites have the advantages of good specific strength and specific modulus, good dimensional stability, excellent fatigue resistance and creep resistance, and are mainly used in aerospace, chemical, energy and other fields. [0003] At present, the preparation methods of C / SiC ceramic matrix composites mainly include slurry infiltration method, precursor impregnation cracking method (Precursor Infiltration and Pyrolysis, PIP), melt infiltration process, chemical vapor infiltration / deposition process (Chemical Vapor Infiltration and Deposition...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): C04B35/80C04B35/565C04B35/622
Inventor 张长瑞胡海峰张玉娣周长城曹英斌
Owner NAT UNIV OF DEFENSE TECH
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