Looking for breakthrough ideas for innovation challenges? Try Patsnap Eureka!

Preparation method of carbon/silicon carbide-zirconium carbide ceramic-based composite material

A technology of carbon composite materials and silicon-zirconium alloys, which is applied to ceramic products, other household appliances, household appliances, etc., can solve the problems of uneven distribution of matrix, uneven density of inner and outer layers, incomplete penetration of alloys, etc., and achieve short preparation cycle , the effect of less amount of citrate

Active Publication Date: 2021-02-05
AEROSPACE INST OF ADVANCED MATERIALS & PROCESSING TECH
View PDF18 Cites 3 Cited by
  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0007] The technical problem to be solved in the present invention is to prepare carbon / carbon composite materials based on the traditional chemical vapor deposition method, which can easily lead to uneven density of the inner and outer layers, and more closed cells at the same time, resulting in the inability of the alloy to completely infiltrate in the subsequent reaction infiltration , and eventually there will be uneven matrix distribution, which will affect the performance of ceramic matrix composites.

Method used

the structure of the environmentally friendly knitted fabric provided by the present invention; figure 2 Flow chart of the yarn wrapping machine for environmentally friendly knitted fabrics and storage devices; image 3 Is the parameter map of the yarn covering machine
View more

Image

Smart Image Click on the blue labels to locate them in the text.
Viewing Examples
Smart Image
  • Preparation method of carbon/silicon carbide-zirconium carbide ceramic-based composite material
  • Preparation method of carbon/silicon carbide-zirconium carbide ceramic-based composite material
  • Preparation method of carbon/silicon carbide-zirconium carbide ceramic-based composite material

Examples

Experimental program
Comparison scheme
Effect test

preparation example Construction

[0033] The present invention provides a kind of preparation method of porous carbon / carbon composite material in the first aspect, described preparation method comprises the following steps:

[0034] (1) Provide carbon fiber prefabricated body;

[0035] (2) Using citrate as a precursor, a porous carbon matrix with pores is formed inside the carbon fiber prefabricated body by a precursor dipping and cracking method;

[0036] (3) soak the porous carbon matrix in a hydrochloric acid solution, remove the carbonate formed by sintering inside the lime by chemical reaction, and obtain a porous carbon / carbon composite material from which the carbonate is removed;

[0037] (4) drying the porous carbon / carbon composite material obtained in step (3) to obtain a dry porous carbon / carbon composite material;

[0038] (5) Repeat steps (2) to (4) at least once to obtain the porous carbon / carbon composite material.

[0039] According to some preferred embodiments, in step (1), the carbon fib...

Embodiment 1

[0066] S1. Pretreatment: Place a commercially purchased carbon fiber fiber prefabricated body (purchased from Jiangsu Tianniao Company) in a high-temperature furnace, feed nitrogen gas with a gas flow rate of 1000 sccm, raise the temperature to 1700°C, and keep the temperature constant for 10 hours to remove residual pollution on the surface things.

[0067] S2. Preparation of the porous carbon matrix: the above preform was immersed in a precursor solution prepared by sodium citrate and deionized water at a mass ratio of 1:0.5, and vacuum impregnated for 60 minutes. After taking out, the obtained material was placed in a high-temperature cracking furnace, and raised to 700° C. under the protection of nitrogen to ensure that the sodium citrate was fully cracked, and a porous carbon matrix was prepared.

[0068] S3. Introduce hydrochloric acid to remove the sodium carbonate particles formed inside: soak the porous carbon matrix in 0.1mol / L HCl solution for a reaction time of 60 ...

Embodiment 2

[0074] This embodiment 2 is basically the same as embodiment 1, the difference is:

[0075] In S2, the cracking temperature of sodium citrate is 800°C.

[0076] Results: A porous carbon / carbon composite material with higher crystallinity and higher reaction degree than in Example 1 was obtained. The XRD of the porous carbon / carbon composite is as follows image 3 shown.

the structure of the environmentally friendly knitted fabric provided by the present invention; figure 2 Flow chart of the yarn wrapping machine for environmentally friendly knitted fabrics and storage devices; image 3 Is the parameter map of the yarn covering machine
Login to View More

PUM

PropertyMeasurementUnit
Densityaaaaaaaaaa
Densityaaaaaaaaaa
Densityaaaaaaaaaa
Login to View More

Abstract

The invention relates to a preparation method of a carbon / silicon carbide zirconium carbide ceramic-based composite material. According to the preparation method, a porous carbon matrix with relatively uniform pore distribution can be formed in the carbon fiber preform, so that more alloys can be infiltrated into the matrix, and the carbon / silicon carbide zirconium carbide ceramic-based compositematerial with uniform distribution in the matrix is obtained; the problems of poor performance stability and the like caused by non-uniform matrix distribution in the carbon / silicon carbide zirconiumcarbide composite material are solved.

Description

technical field [0001] The invention relates to the technical field of ceramic matrix composite materials, in particular to a method for preparing a carbon / silicon carbide-zirconium carbide ceramic matrix composite material. Background technique [0002] With the rapid development of space vehicles, higher requirements are put forward for the working temperature and service time of thermal structural components of the vehicle. As a high-performance thermal protection material, ceramic matrix composites can maintain a very low ablation rate under the harsh conditions of high temperature and high-speed oxidizing airflow, so as to better meet the requirements of spacecraft and rocket engine nozzles. Wait for the needs of the aircraft. [0003] Carbon fiber toughened ceramic matrix composites, taking into account the low density, small thermal expansion coefficient, high dimensional stability of carbon / carbon composites and a series of advantages of ceramics such as high streng...

Claims

the structure of the environmentally friendly knitted fabric provided by the present invention; figure 2 Flow chart of the yarn wrapping machine for environmentally friendly knitted fabrics and storage devices; image 3 Is the parameter map of the yarn covering machine
Login to View More

Application Information

Patent Timeline
no application Login to View More
IPC IPC(8): C04B35/83C04B35/65C04B35/52C04B38/00C04B35/80C04B35/573C04B35/56
CPCC04B35/521C04B35/83C04B38/00C04B35/65C04B35/573C04B35/5622C04B2235/661C04B2235/40C04B2235/6562C04B2235/6565Y02T50/40
Inventor 杨良伟王鹏宋环君李晓东金鑫于艺霍鹏飞刘俊鹏于新民
Owner AEROSPACE INST OF ADVANCED MATERIALS & PROCESSING TECH
Who we serve
  • R&D Engineer
  • R&D Manager
  • IP Professional
Why Patsnap Eureka
  • Industry Leading Data Capabilities
  • Powerful AI technology
  • Patent DNA Extraction
Social media
Patsnap Eureka Blog
Learn More
PatSnap group products

Browse by: Latest US Patents, China's latest patents, Technical Efficacy Thesaurus, Application Domain, Technology Topic, Popular Technical Reports.

© 2024 PatSnap. All rights reserved.Legal|Privacy policy|Modern Slavery Act Transparency Statement|Sitemap|About US| Contact US: help@patsnap.com