A kind of sic/sic composite material high density multilayer matrix and preparation method

A composite material and matrix technology, which is applied in the field of composite material preparation, can solve problems such as consumption of crack energy, single structure, difficulty in meeting the high strength, toughness and stress requirements of aero-engines, and achieve the effect of reducing open porosity

Active Publication Date: 2022-07-05
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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  • A kind of sic/sic composite material high density multilayer matrix and preparation method
  • A kind of sic/sic composite material high density multilayer matrix and preparation method
  • A kind of sic/sic composite material high density multilayer matrix and preparation method

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Effect test

preparation example Construction

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

[0042] In step 1.1, a SiC fiber braid is used to prepare a boron nitride (BN) interface phase on its surface, and the thickness of the interface phase is 300-500 nm.

[0043] In step 1.2, a CVI process is used to prepare a SiC matrix with a certain volume fraction in the SiC fiber preform obtained in step 1.1. Using trichloromethylsilane (MTS) as the precursor, hydrogen as the carrier gas, 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. This results in a porosity of 28 to 36% and a density of 1.7 to 2.1 g / 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 to 500 nm and a volume fraction of 10 vol.% into HF acid, and magnetically stir at roo...

Embodiment 1

[0064] Step 1. Preparation of SiC / SiC preform:

[0065] In step 1.1, a SiC fiber braid is used to prepare a boron nitride (BN) interface phase on its surface, and the thickness of the interface phase is 300-500 nm.

[0066] In step 1.2, a CVI process is used to prepare a SiC matrix with a certain volume fraction in the SiC fiber preform obtained in step 1.1. Using trichloromethylsilane (MTS) as the precursor, hydrogen as the carrier gas, 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. This results in a porosity of 28 to 36% and a density of 1.7 to 2.1 g / cm 3 Porous SiC / SiC composites for subsequent slurry impregnation.

[0067] Step 2. Configure 300-500nm SiC particle water-based slurry:

[0068] Step 2.1 Add SiC particles with a particle size of 300 to 500 nm and a volume fraction of 10 vol.% into HF acid, and magnetically stir at roo...

Embodiment 2

[0088] Step 1. Preparation of SiC / SiC preform:

[0089] In step 1.1, a SiC fiber braid is used to prepare a boron nitride (BN) interface phase on its surface, and the thickness of the interface phase is 300-500 nm.

[0090] In step 1.2, a CVI process is used to prepare a SiC matrix with a certain volume fraction in the SiC fiber preform obtained in step 1.1. Using trichloromethylsilane (MTS) as the precursor, hydrogen as the carrier gas, 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. This results in a porosity of 28 to 36% and a density of 1.7 to 2.1 g / cm 3 Porous SiC / SiC composites for subsequent slurry impregnation.

[0091] Step 2. Configure 300-500nm SiC particle water-based slurry:

[0092] Step 2.1 Add SiC particles with a particle size of 300 to 500 nm and a volume fraction of 10 vol.% into HF acid, and magnetically stir at roo...

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Abstract

The invention relates to a high-density multi-layer matrix of SiC / SiC composite material and a preparation method. p ) The slurry was introduced into the porous SiC / SiC composite material by vacuum impregnation and pressure impregnation, and then a certain content of pyrolytic carbon was prepared in the porous SiC / SiC composite material by the CVI method to make it evenly wrap the SiC particles. The densification of SiC / SiC composites was accomplished by the reaction of pyrolytic carbon and molten silicon by RMI method. The sequential introduction of SiC particles with different particle sizes forms a layered structure, which has a genetic effect on the subsequent preparation of PyC and SiC matrix, and obtains a uniform and high volume fraction of SiC matrix phase, which increases the density of the composite material and increases the energy of crack propagation. Effectively improve the mechanical properties of composite materials. The composite material prepared by this method has a SiC matrix phase with high volume fraction and uniform distribution, high mechanical properties and low open porosity, which solves the problem of low SiC phase content and uneven distribution and strong toughness in the SiC / SiC matrix prepared by the current RMI process. insufficient problem.

Description

technical field [0001] The invention belongs to a preparation method of a composite material, and relates to a high-density multi-layer matrix of a SiC / SiC composite material and a preparation method. Background technique [0002] SiC / SiC composites have great application prospects in aerospace thermal structural components and other fields due to their many advantages such as high temperature resistance, wear resistance, corrosion resistance, high specific strength, high specific modulus, high toughness, and creep resistance. With the continuous development of my country's aerospace industry, the engine thrust-to-weight ratio has gradually increased, the high bypass ratio and total pressure ratio have continued to increase, higher service temperatures, higher stress requirements and corrosive environments. SiC is used for engine hot end structural components. / SiC composites put forward higher strength and toughness, higher damage tolerance, and higher density requirements. ...

Claims

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Application Information

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Patent Type & Authority Patents(China)
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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