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C/ZrC-SiC ultrahigh-temperature ceramic-based composite material and preparation method thereof

A technology of ultra-high temperature ceramics and composite materials, applied in the field of C/ZrC-SiC ultra-high temperature ceramic matrix composite materials and its preparation, can solve problems such as high risk of delamination, achieve wide application prospects, excellent anti-oxidation and ablation resistance , The effect of strong process applicability

Active Publication Date: 2021-02-09
AEROSPACE INST OF ADVANCED MATERIALS & PROCESSING TECH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

However, the preparation method in this patent application is limited by the prepreg compression molding process. When using this method to prepare large-sized and thick components, the risk of delamination during the thermal cracking process is relatively high. Therefore, this method is only suitable for simple structures and walls. thinner member

Method used

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  • C/ZrC-SiC ultrahigh-temperature ceramic-based composite material and preparation method thereof
  • C/ZrC-SiC ultrahigh-temperature ceramic-based composite material and preparation method thereof
  • C/ZrC-SiC ultrahigh-temperature ceramic-based composite material and preparation method thereof

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preparation example Construction

[0027] In a first aspect, the present invention provides a method for preparing a C / ZrC-SiC ultra-high temperature ceramic matrix composite material, the method comprising the following steps:

[0028] (1) Provide n parts of carbon cloth and n-1 parts of ZrC (zirconium carbide) powder, and lay a layer of ZrC powder layer on the carbon cloth layer after each layer of carbon cloth layer. A powdered carbon fiber prefabricated body formed by alternating layers of cloth layers and ZrC powder layers; ZrC powder layer, that is, nano-ZrC ultra-high temperature ceramic powder is added in the layering process of carbon cloth to obtain a powdered carbon fiber preform added with ZrC powder; specifically, in the present invention, a powdered carbon fiber preform is prepared The method is: the carbon cloth layer and the ZrC (zirconium carbide) powder layer are laid alternately in the XY direction of the powdered carbon fiber prefabricated body, and the carbon cloth layer is used between the...

Embodiment 1

[0048] ① Preparation of powdered carbon fiber prefabricated body with carbon cloth laminated suture structure, the preparation method is to alternately superimpose layers of one layer of carbon cloth + one layer of ZrC powder, and then form a powdered carbon fiber prefabricated body with a sutured structure by sewing; , the mass ratio of the fiber contained in the carbon cloth in the prefabricated body to the ZrC powder in the prefabricated body is 1:1, and the density of the powdered carbon fiber prefabricated body is 1.10g / cm 3 .

[0049] ②Preparing a C interface layer on the surface of the powdered carbon fiber prefabricated body by chemical vapor deposition process to obtain a low-density C / C composite material, and the density increment of carbon deposition is 0.1g / cm 3 .

[0050] ③ Using the polycarbosilane precursor solution as the impregnation solution, the SiC matrix was densified by the PIP process.

[0051] ④ Densification by 8 cycles of PIP process to obtain C / Zr...

Embodiment 2

[0054] ① Preparation of powdered carbon fiber prefabricated body with carbon cloth laminated suture structure, the preparation method is to alternately superimpose layers of one layer of carbon cloth + one layer of ZrC powder, and then form a powdered carbon fiber prefabricated body with a sutured structure by sewing; , the mass ratio of the fiber contained in the carbon cloth in the prefabricated body to the ZrC powder in the prefabricated body is 1:0.2.

[0055] ②Preparing a C interface layer on the surface of the powdered carbon fiber prefabricated body by chemical vapor deposition process to obtain a low-density C / C composite material, and the density increment of carbon deposition is 0.1g / cm 3 .

[0056] ③ Using the polycarbosilane precursor solution as the impregnation solution, the SiC matrix was densified by the PIP process.

[0057] ④ Densification by 8 cycles of PIP process to obtain C / ZrC-SiC ultra-high temperature ceramic matrix composites.

[0058] The density o...

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Abstract

The invention relates to a C / ZrC-SiC ultrahigh-temperature ceramic-based composite material and a preparation method thereof. The method comprises the following steps: preparing a powder-added carbonfiber preform by alternately superposing and laying carbon cloth layers and ZrC powder layers; preparing a C interface layer on the surface of the powder-added carbon fiber preform to obtain a low-density C / C composite material; carrying out SiC matrix densification on the low-density C / C composite material through a PIP process with a polycarbosilane precursor solution as impregnation liquid; andrepeating the PIP process multiple times to prepare the C / ZrC-SiC ultrahigh-temperature ceramic-based composite material. The method is high in process applicability, simple in preparation process and easy to operate, the addition amount of ZrC powder in the prepared C / ZrC-SiC ultrahigh-temperature ceramic-based composite material is adjustable and controllable, and the C / ZrC-SiC ultrahigh-temperature ceramic-based composite material has excellent mechanical properties and oxidation resistance and ablation resistance and shows wide application prospects in the field of aerospace and aviation.

Description

technical field [0001] The invention belongs to the technical field of thermal structural composite materials, and in particular relates to a C / ZrC-SiC ultra-high temperature ceramic matrix composite material and a preparation method thereof. Background technique [0002] C / SiC composite materials have a series of excellent properties such as low density, high temperature resistance, high specific modulus, high specific strength and thermal shock resistance, and are widely used in the aerospace field. In order to meet the environmental requirements of higher temperature, ultra-high temperature ceramic components are used to modify the matrix of C / SiC composites to obtain ultra-high temperature ceramic matrix composites. [0003] The preparation methods of ultra-high temperature ceramic matrix composites generally include slurry impregnation and reaction infiltration processes. The slurry method is used to prepare the ultra-high temperature ablation-resistant matrix through ...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): C04B35/80C04B35/84
CPCC04B2235/5248C04B2235/3826C04B2235/3839C04B2235/483C04B2235/77C04B2235/96C04B2235/9684
Inventor 李晓东刘俊鹏霍鹏飞宋环君于新民王涛赵英民
Owner AEROSPACE INST OF ADVANCED MATERIALS & PROCESSING TECH
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