Method of preparing carbon/carbon-silicon carbide ceramics base composite material

A technology of silicon carbide ceramic matrix and composite materials, which is applied in the field of preparation of carbon/carbon-silicon carbide ceramic matrix composite materials, can solve the problems of limited material structure control, etc., to alleviate modulus mismatch, increase energy, and improve toughness Effect

Inactive Publication Date: 2007-09-12
NORTHWESTERN POLYTECHNICAL UNIV
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

From the point of view of mechanical properties, PyC is one of the best crack deflection materials in non-oxide ceramic matrix composites, but there is only one layer of PyC in C / SiC composites, the material structure is limited, and there is a certain degree of further improvement in strength and toughness. limitation

Method used

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Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0015] Embodiment 1: (1) A two-dimensional prefabricated body is prepared by laminating 1K plain weave carbon cloth, and the volume percentage of fibers is 40%;

[0016] (2) With propylene as the source material and argon as the dilution gas, the PyC interface was deposited by chemical vapor infiltration, the deposition temperature was 900 °C, and the deposition time was 100 h;

[0017] (3) Carry out heat treatment on the PyC interface, the heat treatment temperature is 1600°C, and the time is 1h;

[0018] (4) with trichloromethylsilane (CH 3 SiCl 3 , MTS) is the source material, argon is the diluent gas, hydrogen is the carrier gas, H 2 The molar ratio of MTS and MTS is 10:1, the SiC matrix is ​​deposited on the PyC interface by chemical vapor infiltration, the deposition temperature is 1000 ° C, and the deposition time is 40 h;

[0019] (5) Deposit the PyC substrate twice successively on the SiC substrate, and the deposition time is 25 hours each;

[0020] (6) Deposit th...

Embodiment 2

[0026] Embodiment 2: (1) adopt 1K plain weave carbon cloth lamination to prepare two-dimensional prefabricated body, the volume percent of fiber is 43%;

[0027] (2) With propylene as the source material and argon as the diluent gas, the PyC interface was deposited by chemical vapor infiltration method, the deposition temperature was 950 °C, and the deposition time was 150 h;

[0028] (3) Perform heat treatment on the PyC interface, the heat treatment temperature is 1700°C, and the time is 2h;

[0029] (4) with trichloromethylsilane (CH 3 SiCl 3 , MTS) is the source material, argon is the diluent gas, hydrogen is the carrier gas, H 2 The molar ratio to MTS is 10:1, and the SiC substrate is deposited on the PyC interface by chemical vapor infiltration method, the deposition temperature is 1050 ° C, and the deposition time is 40 h;

[0030] (5) Deposit the PyC substrate twice successively on the SiC substrate, and the deposition time is 25 hours each;

[0031] (6) Deposit th...

Embodiment 3

[0037] Embodiment 3: (1) adopt three-dimensional four-step method to weave carbon fiber into three-dimensional prefabricated body, the volume percentage of fiber is 45%;

[0038] (2) With propylene as the source material and argon as the dilution gas, the PyC interface was deposited by chemical vapor infiltration method, the deposition temperature was 1000 ° C, and the deposition time was 200 h;

[0039] (3) Perform heat treatment on the PyC interface, the heat treatment temperature is 1800°C, and the time is 3h;

[0040] (4) with trichloromethylsilane (CH 3 SiCl 3 , MTS) is the source material, argon is the diluent gas, hydrogen is the carrier gas, H 2 The molar ratio to MTS is 10:1, and the SiC substrate is deposited on the PyC interface by chemical vapor infiltration method, the deposition temperature is 1100 ° C, and the deposition time is 80 h;

[0041] (5) Deposit the PyC substrate on the SiC substrate, the deposition time is 25h;

[0042] (6) Deposit the SiC substra...

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Abstract

This invention discloses a preparation method for preparing C / C-SiC ceramic base compound material, which first of all deposits a pyrogenated carbon interface layer on the surface of a carbon fiber prefabricated body, then deposits pyrogenated carbon and SiC alternately to form a multi-layer (PyC / SiC)n matrix to get the C / C-SiC compound material. Since this invention applies PyC matrix to replace part of SiC matrix to form a multi-layer matrix, the dismatch of modulus between fiber and the matrix is released, when the PyC layer deflects, the crack peak stress is released steadily and energy cost by breakage is increased, and obdurability of the compound material is increased, the downward tensible-strength of 2-D C / C-SiC compound material is increased to 285.70-290.45MPa from 281.80MPa under room temperature, the downward fracture power of that under room temperature is increased to 12.50-13.64KJ.m-2 from 10.00KJm-2 and the tensible-strength is increased to 385.78-396.67MPa from 323.00MPa and control to C / C-SiC compound material micro-sturcture can be realized by controlling deposition time and times to control thickness and layers of the matrix.

Description

technical field [0001] The invention relates to a preparation method of a carbon / carbon-silicon carbide ceramic matrix composite material. Background technique [0002] C / SiC ceramic matrix composites have a series of excellent properties such as low density, high strength, high temperature resistance, ablation resistance and erosion resistance, and have a wide range of application potentials in the aerospace field. With the development of aerospace technology, there are more and more types of components that need to be made of C / SiC composite materials, and the working conditions of these components are different, such as: the leading edge of the wing requires high strength materials, the combustion chamber and the nozzle Tubes require materials with high toughness, while drive bearings for composite flaps require materials with both high strength and high toughness. Therefore, different requirements are put forward for the mechanical properties of C / SiC composites, especi...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): C04B35/622C04B35/565C04B35/52
Inventor 张立同成来飞徐永东刘小瀛王东韩秀峰孟志新
Owner NORTHWESTERN POLYTECHNICAL UNIV
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