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A kind of preparation method of multi-component toughened silicon carbide ceramic matrix composite material

A silicon carbide ceramic matrix and composite material technology, applied in the direction of weight reduction, can solve the problems of difficult densification of composite materials, poor dispersion stability of nanoparticles, uncontrollable growth of whiskers, etc., and achieves low cost and high interface bonding strength. , reduce the effect of corrosion

Active Publication Date: 2022-07-12
AVIC BEIJING INST OF AERONAUTICAL MATERIALS
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Application numbers CN201810193507.1 and CN200910129807.4 etc. use ternary layered Ti 3 SiC 2 To toughen SiC ceramic matrix composites, the toughening effect is limited due to the single toughening mechanism
Application numbers CN201710948861.6 and CN201610110058.0 all use SiC whiskers to toughen silicon carbide ceramic matrix composites. The former uses simple mechanical mixing to introduce SiC whiskers into the silicon carbide matrix. On the one hand, mechanical mixing has a significant impact on material properties. On the other hand, due to the cross-connection effect between whiskers, it is difficult to densify the composite material.
The latter uses the in-situ growth method to synthesize whiskers in the SiC matrix, and the growth of whiskers in this method is relatively uncontrollable.
In addition, there is also the purpose of toughening by introducing nanoparticles or carbon nanotubes into SiC. These methods use mechanical mixing to introduce toughening phases. In addition, the dispersion stability of nanoparticles is poor.

Method used

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Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0025] Step 1: Mix 20g metal Ti powder (particle size 0.5μm, purity 99.9%), 0.4g powder dispersant, 150g absolute ethanol and 50g phenolic resin, ball mill for 12h to prepare a mixed slurry;

[0026] Step 2: apply the mixed slurry prepared in step 1 on the SiC fiber fabric containing the interface layer, and remove the anhydrous ethanol by evaporation under reduced pressure to prepare a prepreg;

[0027] Step 3: place the prepreg obtained in step 2 in a mold and use a hot press to cure and form, set the curing temperature to 220° C., the pressure to be 0.2 MPa, and the time to be 5 hours to obtain a preform;

[0028] Step 4: carbonizing the preform obtained in step 3 at 1000° C. in an inert atmosphere for 60 minutes to obtain a porous body;

[0029] Step 5: under vacuum conditions, infiltrate Si (99.99%) and B (99.99%) alloy powders with a mass ratio of 50:1 into the porous body, wherein the mass ratio of Si-B alloy to the porous body is 5:1. The infiltration temperature is 1...

Embodiment 2

[0031] Step 1: Mix 35g TiC (particle size 1 μm, purity 99.9%), 0.7g powder dispersant, 180g mixture of isopropanol and butyl acetate (mass ratio 1:2) and 80g furan resin, ball mill for 24h to make the mixture slurry;

[0032] Step 2: apply the mixed slurry prepared in step 1 on the C fiber fabric containing the interface layer, and remove the mixture of isopropanol and butyl acetate by evaporation under reduced pressure to prepare a prepreg;

[0033] Step 3: place the prepreg obtained in step 2 in a mold and use a hot press to cure and form, set the curing temperature to 150°C, the pressure to 0.5MPa, and the time to 2.5h to obtain a preform;

[0034] Step 4: carbonizing the preform obtained in step 3 at 800° C. in an inert atmosphere for 120 min to obtain a porous body;

[0035] Step 5: under vacuum conditions, infiltrate Si (99.99%) and B (99.99%) alloy powders with a mass ratio of 30:1 into the porous body, wherein the mass ratio of Si-B alloy to the porous body is 2.5:1. ...

Embodiment 3

[0037] Step 1: Mix 50g TiC (particle size 5μm, purity 99.9%), 1g powder dispersant, 200g xylene and 100g phenolic resin derivative, and ball mill for 30h to prepare a mixed slurry;

[0038] Step 2: apply the mixed slurry prepared in step 1 on the SiC fiber fabric containing the interface layer, and remove the xylene by vacuum evaporation to prepare a prepreg;

[0039] Step 3: Place the prepreg obtained in Step 2 in a mold and use a hot press to cure and form, set the curing temperature to 300°C, the pressure to 12MPa, and the time to 1h to obtain a preform;

[0040] Step 4: carbonizing the preform obtained in step 3 at 1200° C. in an inert atmosphere for 30 minutes to obtain a porous body;

[0041] Step 5: under vacuum conditions, infiltrate Si (99.9%) and B (99.9%) alloy powders with a mass ratio of 10:1 into the porous body, wherein the mass ratio of Si-B alloy to the porous body is 3:1. The infiltration temperature is 1420℃, and the reaction time is 40min, thereby obtainin...

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Abstract

The invention belongs to the technical field of preparation of ceramic matrix composite materials, in particular to a preparation method of a multi-component toughened silicon carbide ceramic matrix composite material. The method is based on the reactive infiltration process. The metal Ti powder or TiC powder is mixed into the matrix slurry for preparing silicon carbide ceramic matrix composites, and after the prepreg is prepared with the fiber, the porous body is obtained by successively curing and carbonization. The Si-B alloy is melted and infiltrated into the porous body at high temperature, and Ti or TiC reacts with C and B to generate Ti in situ in the SiC matrix 3 SiC 2 and TiB 2 The toughening phase is obtained to obtain a multi-strengthened fiber-reinforced silicon carbide ceramic matrix composite material. This method utilizes Ti 3 SiC 2 The layered structure of the grain itself, combined with TiB 2 The columnar structure of the grains and the synergy of the two toughening mechanisms will further improve the toughness of the ceramic matrix composites.

Description

technical field [0001] The invention belongs to the technical field of preparation of ceramic matrix composite materials, in particular to a preparation method of a multi-component toughened silicon carbide ceramic matrix composite material. Background technique [0002] Fiber-reinforced silicon carbide ceramic matrix composites have a series of excellent properties such as high specific strength, high specific modulus, high temperature resistance and ablation resistance, and have broad application prospects in aviation, aerospace and other fields. For some specific application parts, materials are required to have special functional properties, such as rotating parts of aero-engines, etc., and composite materials are required to have higher toughness. Due to the brittleness of the SiC matrix itself, it is not conducive to the weakening and deflection of defects such as cracks under load. Therefore, from the perspective of material design, the toughening of composite materi...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): C04B35/80C04B35/84C04B35/622C04B35/565
CPCC04B35/622C04B35/573C04B2235/5244C04B2235/5248C04B2235/404C04B2235/3843C04B2235/3813C04B2235/3817C04B2235/40Y02T50/40
Inventor 周怡然焦健高晔姜卓钰吕晓旭杨金华刘虎
Owner AVIC BEIJING INST OF AERONAUTICAL MATERIALS
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