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SiC/SiC composite material high-density multilayer matrix and preparation method thereof

A composite material and matrix technology, which is applied in the field of composite material preparation, can solve the problems of crack energy consumption, crack deflection, single structure, etc., and achieve the effect of reducing open porosity

Active Publication Date: 2021-12-07
NORTHWESTERN POLYTECHNICAL UNIV
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

The matrix prepared by the RMI method is generally a homogeneous or doped modified phase, with a single structure, which cannot achieve good crack deflection, consumes crack energy, and achieves a high-toughness matrix to meet the requirements of the thermal shock resistance of aeroengines. For example, Wang et al. The dense SiC / SiC composite material prepared by reactive melt infiltration (RMI) technology has a bending strength of 288.2±0.88MPa and a fracture toughness of 16.0±0.25GPa, which is difficult to meet the high-strength-toughness stress requirements of aero-engines

Method used

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  • SiC/SiC composite material high-density multilayer matrix and preparation method thereof
  • SiC/SiC composite material high-density multilayer matrix and preparation method thereof
  • SiC/SiC composite material high-density multilayer matrix and preparation method thereof

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preparation example Construction

[0041] Step 1. Preparation of SiC / SiC preform:

[0042] In step 1.1, a boron nitride (BN) interface phase is prepared on the surface of the SiC fiber braided body, and the thickness of the interface phase is 300-500 nm.

[0043] Step 1.2 Prepare a certain volume fraction of the SiC matrix in the SiC fiber preform obtained in step 1.1 by using the CVI process. Using trichloromethylsilane (MTS) as the precursor, hydrogen as the carrier gas, and argon as the diluent gas, the flow ratio of the three is 1:5-50:2-20, the total pressure is 0.5-5kPa, and the deposition temperature is 873 ~1773K, the deposition time is about 600 hours. Thus, the porosity is 28-36%, and the density is 1.7-2.1g / cm 3 porous SiC / SiC composites for subsequent slurry impregnation.

[0044] Step 2. Configure 300-500nm SiC particle water-based slurry:

[0045] Step 2.1 Add SiC particles with a particle size of 300-500 nm and a volume fraction of 10 vol.% to HF acid, and stir magnetically at room temperatur...

Embodiment 1

[0065] Step 1. Preparation of SiC / SiC preform:

[0066] In step 1.1, a boron nitride (BN) interface phase is prepared on the surface of the SiC fiber braided body, and the thickness of the interface phase is 300-500 nm.

[0067] Step 1.2 Prepare a certain volume fraction of the SiC matrix in the SiC fiber preform obtained in step 1.1 by using the CVI process. Using trichloromethylsilane (MTS) as the precursor, hydrogen as the carrier gas, and argon as the diluent gas, the flow ratio of the three is 1:5-50:2-20, the total pressure is 0.5-5kPa, and the deposition temperature is 873 ~1773K, the deposition time is about 600 hours. Thus, the porosity is 28-36%, and the density is 1.7-2.1g / cm 3 porous SiC / SiC composites for subsequent slurry impregnation.

[0068] Step 2. Configure 300-500nm SiC particle water-based slurry:

[0069] Step 2.1 Add SiC particles with a particle size of 300-500 nm and a volume fraction of 10 vol.% to HF acid, and stir magnetically at room temperatur...

Embodiment 2

[0089] Step 1. Preparation of SiC / SiC preform:

[0090] In step 1.1, a boron nitride (BN) interface phase is prepared on the surface of the SiC fiber braided body, and the thickness of the interface phase is 300-500 nm.

[0091] Step 1.2 Prepare a certain volume fraction of the SiC matrix in the SiC fiber preform obtained in step 1.1 by using the CVI process. Using trichloromethylsilane (MTS) as the precursor, hydrogen as the carrier gas, and argon as the diluent gas, the flow ratio of the three is 1:5-50:2-20, the total pressure is 0.5-5kPa, and the deposition temperature is 873 ~1773K, the deposition time is about 600 hours. Thus, the porosity is 28-36%, and the density is 1.7-2.1g / cm 3 porous SiC / SiC composites for subsequent slurry impregnation.

[0092] Step 2. Configure 300-500nm SiC particle water-based slurry:

[0093] Step 2.1 Add SiC particles with a particle size of 300-500 nm and a volume fraction of 10 vol.% to HF acid, and stir magnetically at room temperatur...

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Abstract

The invention relates to a SiC / SiC composite material high-density multilayer matrix and a preparation method thereof. Prepared SiC particle (SiCp) slurry is introduced into a porous SiC / SiC composite material through vacuum impregnation and pressure impregnation methods, then a certain content of pyrolytic carbon is prepared in the porous SiC / SiC composite material by adopting a CVI method, the SiC particles are uniformly wrapped by the pyrolytic carbon, and finally, densification of the SiC / SiC composite material is completed through reaction of pyrolytic carbon and molten silicon by adopting an RMI method. SiC particles with different particle sizes are sequentially introduced to form a layered structure, so that a genetic effect is generated on subsequently prepared PyC and SiC matrixes, a uniform SiC matrix phase with a high volume fraction is obtained, the density of the composite material is increased, the energy of crack propagation is increased, and the mechanical property of the composite material is effectively improved. The composite material prepared by the method has a SiC matrix phase with high volume fraction and uniform distribution, high mechanical property and low open porosity, and solves the problems of low SiC phase content, non-uniform distribution and insufficient toughness in the SiC / SiC matrix prepared by the existing RMI process method.

Description

technical field [0001] The invention belongs to a preparation method of a composite material, and relates to a SiC / SiC composite material high-density multilayer matrix and a preparation method. Background technique [0002] Due to its high temperature resistance, wear resistance, corrosion resistance, high specific strength, high specific modulus, high toughness, creep resistance and many other advantages, SiC / SiC composite materials have great application prospects in aerospace thermal structural components and other fields. With the continuous development of my country's aerospace industry, the thrust-to-weight ratio of the engine is gradually increasing, the high bypass ratio, the total pressure ratio are constantly increasing, the service temperature is higher, the stress requirements are higher, and the corrosive environment, SiC is used for the hot end structural parts of the engine / SiC composites require higher strength and toughness, higher damage tolerance, and hig...

Claims

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Application Information

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IPC IPC(8): C04B35/577C04B35/80C04B35/622
CPCC04B35/565C04B35/80C04B35/622C04B2235/614C04B2235/616C04B2235/5244C04B2235/386C04B2235/5445C04B2235/5436C04B2235/428Y02E30/30
Inventor 成来飞叶昉郭广达宋超坤张立同
Owner NORTHWESTERN POLYTECHNICAL UNIV
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