Process for preparing carbon/silicon carbide composite material

A composite material, silicon carbide technology, applied in the field of composite material preparation, can solve problems such as poor shear resistance between layers

Active Publication Date: 2009-01-07
NORTHWESTERN POLYTECHNICAL UNIV
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0003] In order to overcome the disadvantages of poor interlayer shear resistance in the prior art, the present invention provides a method for preparing carbon/silicon carbide composite

Method used

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  • Process for preparing carbon/silicon carbide composite material
  • Process for preparing carbon/silicon carbide composite material
  • Process for preparing carbon/silicon carbide composite material

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0016] Example 1: Preparation of a C / SiC composite material with a puncture spacing of 2 mm and an interface phase thickness of 0.16 μm.

[0017] Select T300-1K carbon fiber with a diameter of 7 μm in carbon fiber 1, weave it into plain weave 3, superimpose 30 layers, and sew the laminated layers together by puncture suture method to obtain a puncture distance 7 and a puncture step length 8 of 2 mm, and a volume density of 0.70g / cm 3 1. A carbon fiber prefabricated body with a carbon fiber volume fraction of 40.0%.

[0018] The carbon fiber prefabricated body was clamped with a graphite clamp, and placed in a vacuum furnace for degumming and pretreatment at 1800 ° C for 3 h.

[0019] The resulting fiber preforms were deposited with PyC using CVI. The preparation of the PyC interfacial phase uses propylene as the source gas, Ar as the diluent gas, and H 2 It is the carrier gas, the deposition temperature is 900°C, and the total system pressure is 5KPa. Get a density of 0.80...

Embodiment 2

[0023] Example 2: Preparation of a C / SiC composite material with a puncture spacing of 4 mm and an interface phase thickness of 0.2 μm.

[0024] Select T300-1K carbon fiber with a diameter of 7 μm in carbon fiber 1, weave it into plain weave 3, superimpose 40 layers, and sew the stacked layers together by puncture suture method, and obtain the puncture distance 7 and puncture step length 8, both of which are 4mm, and the volume density is 0.73g / cm 3 , A carbon fiber preform with a carbon fiber volume fraction of 41.7%.

[0025] The carbon fiber prefabricated body was clamped with a graphite clamp, and placed in a vacuum furnace for degumming and pretreatment at 1900°C for 2.5 hours.

[0026] The resulting fiber preforms were deposited with PyC using CVI. The preparation of the PyC interfacial phase uses propylene as the source gas, Ar as the diluent gas, and H 2 It is the carrier gas, the deposition temperature is 950°C, and the total system pressure is 5KPa. The obtained ...

Embodiment 3

[0031] Example 3: Preparation of a C / SiC composite material with a puncture distance of 6 mm and an interface phase thickness of 0.2 μm.

[0032] Select T300-1K carbon fiber with a diameter of 7 μm in carbon fiber 1, weave it into plain weave 3, superimpose 55 layers, and sew the laminated layers together by puncture suture method, and obtain the puncture distance 7 and puncture step length 8 of 6 mm, and the volume density is 0.71g / cm 3 , A carbon fiber prefabricated body with a carbon fiber volume fraction of 40.3%.

[0033] The carbon fiber prefabricated body was clamped with a graphite clamp, and placed in a vacuum furnace at 2100°C for 2 hours of degumming and pretreatment.

[0034] The resulting fiber preforms were deposited with PyC using CVI. The preparation of the PyC interfacial phase uses propylene as the source gas, Ar as the diluent gas, and H 2 It is the carrier gas, the deposition temperature is 1000°C, and the total system pressure is 7KPa. The resulting de...

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Abstract

The invention discloses a preparation method for a carbon/carborundum composite material. Firstly, carbon fibre is woven into single-layer plain cloth; a plurality of layers of the plain cloth are superposed, and are punctured and stitched with carbon fiber, thus forming a prefabricated carbon fiber body. The prefabricated carbon fiber body is arranged in a vacuum furnace and boiled off as well as pretreated; subsequently, pyrolytic carbon deposits, thus getting the C/C composite material; the multihole C/C composite material is heated; a SiC basal body is impregnated in the treated C/C composite material by adopting the CVI method, thus getting the C/SiC composite material. As the C/SiC composite material is prepared by puncturing and stitching the prefabricated carbon fiber body in combination of the CVI method. The interlaminar shear strength of the C-SiC composite material at 1200 DEG C is increased to 36 to 49MPa from 22 to 24MPa of the prior art; the tensile strength is increased to 275 to 345MPa from 220 to 300MPa of the prior art.

Description

technical field [0001] The invention relates to a preparation method of a composite material. Background technique [0002] Literature "Sung R. Choi, Anthony M. Calomino, Narottam P. Bansal, and Michael J. Verrilli. LifeLimiting Behavior in Interlaminar Shear of Continuous Fiber-Reinforced Ceramic Matrix Composites at Elevated Temperatures. NASA technical report, NASA / TM-2006-214088 .” discloses a method for preparing two-dimensional laminated C / SiC composites using chemical vapor infiltration (CVI). This method prepares components with complex shapes, close dimensions, and high fiber volume fractions. Moreover, through the rational design and control of the pyrolytic carbon (PyC) interface layer in the composite material, the performance of the composite material can be optimized and the damage to the fiber can be effectively overcome. However, the tensile strength of the two-dimensional laminated C / SiC composite is only 220-300 MPa; the interlayer shear resistance is poor...

Claims

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Application Information

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IPC IPC(8): C04B35/83
Inventor 徐永东张立同成来飞殷小玮聂景江
Owner NORTHWESTERN POLYTECHNICAL UNIV
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