Preparation method for in-situ generated Ti3SiC2-phase toughening silicon carbide ceramic matrix composite material

A technology for toughened silicon carbide and composite materials, which is applied in the field of preparation of in-situ Ti3SiC2 phase toughened silicon carbide ceramic matrix composite materials, can solve problems such as poor process stability, unfavorable engineering production, and complicated preparation process, and achieve Effects of high fracture toughness and damage tolerance, less fiber damage, and low manufacturing cost

Inactive Publication Date: 2018-08-17
AVIC BEIJING INST OF AERONAUTICAL MATERIALS
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

The above method involves three processes of CVI, SI and MI successively, and the generated Ti 3 SiC 2 The dispersibility of CVI is restricted by the pore distribution of the C / C prefabricated body produced by the CVI process. The preparation process is complicated, the cycle is long, the process stability is not good, and it is not conducive to engineering production
In addition, its infiltration temperature is higher than 1500 °C, which is only suitable for high temperature resistant fiber reinforcements such as carbon fibers.

Method used

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Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0040] Step 1: Add 70g of phenolic resin to 350g of ethanol and stir until completely dissolved, then add 70g of TiC powder with a particle size of 10μm, stir evenly, pour into a ball mill tank, and make a mixed slurry after ball milling for 24 hours;

[0041] Step 2: immerse the SiC2D fabric with the BN / SiC interface layer in the slurry prepared in step 1 to prepare a prepreg;

[0042]Step 3: Cut the prepreg obtained in Step 2 into a size of 16cm×16cm, and the volume fraction of fiber is 39%. Further hot pressing molding, the hot pressing temperature is 290 ° C, the pressure is 10 MPa, and the time is 2 hours, to obtain the preform;

[0043] Step 4: Put the preform obtained in Step 3 into an argon atmosphere, and crack it at 1200° C. for 30 minutes. A SiC / C-TiC porous body with a size of 16cm×16cm×3cm was prepared;

[0044] Step 5: Coating Si powder on the surface of the SiC / C-TiC porous body, the mass ratio of Si to porous body is 3.8:1. React at the infiltration temperat...

Embodiment 2

[0047] Step 1: Add 35g of furan resin into 80g of acetone and stir until it is completely dissolved, then add 5g of TiC powder with a particle size of 5 μm, stir evenly, pour it into a ball mill tank, and make a mixed slurry after ball milling for 24 hours;

[0048] Step 2: immerse the SiC2.5D fabric with the BN / SiC / PyC interface layer in the slurry prepared in step 1 to prepare a prepreg;

[0049] Step 3: Cut the prepreg obtained in Step 2 into a size of 8cm×8cm, and the volume fraction of fiber is 50%. Further hot-press forming, the hot-press temperature is 160°C, the pressure is 6MPa, the time is 8h, and the preform is obtained;

[0050] Step 4: Put the preform obtained in Step 3 into an argon atmosphere, and crack it at 1000° C. for 20 minutes. A SiC / C-TiC porous body with a size of 8cm×8cm×5cm was prepared;

[0051] Step 5: wrap Si powder on the surface of SiC / C-TiC porous body, the mass ratio of Si to porous body is 3:1. React at the infiltration temperature of 1460°C...

Embodiment 3

[0054] Step 1: Add 30g of furan resin into 60g of toluene and stir until completely dissolved, then add 6g of TiC powder with a particle size of 10μm, stir evenly, pour into a ball mill tank, and make a mixed slurry after ball milling for 6 hours;

[0055] Step 2: Immerse the carbon fiber 3D fabric with the SiC / PyC interface layer in the slurry prepared in step 1 to prepare a prepreg;

[0056] Step 3: Cut the prepreg obtained in Step 2 into a size of 8cm×8cm, and the volume fraction of fiber is 45%. Further hot-press molding, the hot-press temperature is 260°C, the pressure is 7MPa, and the time is 6h, to obtain the preform;

[0057] Step 4: Put the preform obtained in Step 3 into a nitrogen atmosphere, and crack it at 1400° C. for 5 minutes. A C / C-TiC porous body with a size of 8cm×8cm×3.5cm was prepared;

[0058] Step 5: uniformly wrap Si powder on the surface of the C / C-TiC porous body, the mass ratio of Si to porous body is 2:1. React for 120min at the infiltration temp...

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Abstract

The invention belongs to the technical field of the ceramic matrix composite material preparation, and particularly relates to a preparation method for an in-situ generated Ti3SiC2-phase toughening silicon carbide ceramic matrix composite material. The method comprises the following steps: enabling TiC powder, connection resin and an organic solvent to be prepared as slurry, and preparing prepregwith fibers, to obtain a fiber / C-TiC porous body through hot-pressing and carbonizing, covering the surface of the porous body by using Si powder, and generating Ti3SiC2 in situ in a process of generating a silicon carbide matrix by using a high-temperature melting silicon permeation technology. The method is capable of not only eliminating the residual silicon content in the matrix, but also weakening the adverse effect of silicon to mechanical properties of the composite material; in addition, because of an own stratified structure of a MAX-phase material, while the ceramic matrix compositematerial bears load, a crack is expanded to the layer interface and is hindered so that deflection or passivation is produced, the stress concentration of the point of the crack is weakened, and the toughening to the ceramic matrix composite material is finally realized.

Description

technical field [0001] The invention belongs to the technical field of preparation of ceramic-based composite materials, and in particular relates to a method for preparing in-situ Ti3SiC2 phase toughened silicon carbide ceramic-based composite materials. Background technique [0002] At present, the preparation technology of ceramic matrix composite materials at home and abroad has become mature, and some technical achievements have been successfully applied to the hot end parts of aero-engines. These processes include chemical vapor infiltration (CVI) process, precursor conversion (PIP) process, melt infiltration (MI) process, etc. Among them, the MI process is considered to be an effective process for the rapid and low-cost preparation of near-net shape components with complex shapes. However, a very big problem with this process is that during the melt infiltration process, the existence of residual Si (5vol%-30vol%) seriously affects the high-temperature performance of...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): C04B35/80C04B35/84C04B35/65C04B35/565C04B35/622
CPCC04B35/573C04B35/622C04B35/65C04B35/806C04B2235/3817C04B2235/386C04B2235/5244C04B2235/5248C04B2235/96
Inventor 周怡然刘虎杨金华焦健
Owner AVIC BEIJING INST OF AERONAUTICAL MATERIALS
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