Co-curing forming process of ceramic matrix composite component

A composite material component, curing and molding technology, applied in ceramic products, applications, household appliances, etc., to improve the molding quality and preparation efficiency, avoid damage, and improve the molding quality.

Inactive Publication Date: 2018-10-12
AVIC BEIJING INST OF AERONAUTICAL MATERIALS
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] The present invention provides a co-curing molding process for ceramic matrix composite components to solve the technical problems of forming complex components of ceramic matrix composite materials in the prior art. Material prefabricated body, followed by high-temperature sintering to prepare porous body, and ceramic matrix composite integral components are prepared by fusion silicon infiltration to realize integral molding of complex components

Method used

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  • Co-curing forming process of ceramic matrix composite component
  • Co-curing forming process of ceramic matrix composite component

Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0027] see Figure 1~2 As shown, a process step for preparing a ceramic matrix composite component is as follows:

[0028] Step 1. Cutting the SiC fiber prepreg, laying it according to the layup design of the component forming, and preparing 3 SiC fiber prepreg prefabricated bodies of type A, 2 pieces of type B, 2 pieces of type C and 1 piece of type D;

[0029] Step 2. Put the SiC fiber prepreg Class A preform prepared in Step 1 into the Class A preform tooling, mold and solidify it through a hot press. The molding temperature is 350°C, the molding pressure is 5MPa, and the pressure holding time is 5h , preparing hot-pressed preforms A1, A2 and A3;

[0030] Step 3: Put the Class B preform of SiC fiber prepreg prepared in Step 1 into the Class B preforming tooling, and preform the Class B preform at room temperature. The forming pressure is about 2MPa, and the holding time is 1h , to prepare preforms B1 and B2;

[0031] Step 4. Put the SiC fiber prepreg C-type preform prepa...

Embodiment 2

[0037] A process for preparing ceramic matrix composite components is as follows:

[0038] Step 1. Cutting the SiC fiber prepreg, laying it according to the layup design of the component forming, and preparing 3 SiC fiber prepreg prefabricated bodies of type A, 2 pieces of type B, 2 pieces of type C and 1 piece of type D;

[0039] Step 2. Put the SiC fiber prepreg class A preform prepared in step 1 into the class A preforming tooling, and cure and shape it through an autoclave. The molding temperature is 400°C, the heating rate is 3°C / min, and the molding pressure is about 4MPa, the holding time is about 3h, and the hot-pressed preforms A1, A2 and A3 are prepared;

[0040] Step 3: Put the SiC fiber prepreg B-type preform prepared in step 1 into the B-type preforming tooling, and cure and shape it through an autoclave. The molding process is the same as that of the A-type preform. Body B1 and B2;

[0041] Step 4. Put the SiC fiber prepreg C-type preform prepared in step 1 int...

Embodiment 3

[0047]A process for preparing ceramic matrix composite components is as follows:

[0048] Step 1. Cutting the SiC fiber prepreg, laying it according to the layup design of the component forming, and preparing 3 SiC fiber prepreg prefabricated bodies of type A, 2 pieces of type B, 2 pieces of type C and 1 piece of type D;

[0049] Step 2. Put the SiC fiber prepreg class A preform prepared in step 1 into the class A preforming tooling, and cure and shape it through a vacuum hot pressing bag. The molding temperature is 450 ° C, and the pressure holding time is about 5 hours. Preforms A1, A2 and A3;

[0050] Step 3. Put the SiC fiber prepreg B-type preform prepared in step 1 into B-type preforming tooling, and cure and shape it through a vacuum hot-press bag. The molding temperature is 450°C, and the pressure holding time is about 5 hours. Preforms B1 and B2;

[0051] Step 4. Put the SiC fiber prepreg C-type prefabricated body prepared in step 1 into the C-type preforming toolin...

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Abstract

The invention relates to a co-curing forming process of a ceramic matrix composite component, according to the process, a silicon carbide fiber prepreg is cut and laid out according to a forming and layering design scheme, preforms A, B, C and D are respectively prepared by preforming or hot-press forming, the preforms A, B, C and D are bonded to each other through an adhesion aid system, and prepared into a co-curing member by hot-press curing, and a porous body member is prepared by high-temperature carbonization; the porous body member is prepared into the CMC ceramic matrix composite component reinforced with silicon carbide fiber by molten silicon infiltration. The co-curing forming process can be used for integral forming of ceramic matrix composite complex components, improves the forming quality of the complex components, reduces the manufacturing cost, and is of great significance for improving the service life and performance of the complex components.

Description

technical field [0001] The invention relates to a co-solidification molding process for a ceramic matrix composite material component, which belongs to the technical field of composite material molding and manufacturing. technical background [0002] CMC (Ceramic Matrix Composite) is widely used in high-pressure compressor blades and casings, high-pressure and low-pressure turbine disks and blades, combustion chambers, afterburners, flame stabilizers and exhaust nozzles due to its excellent high temperature resistance. End pieces have important applications. Ceramic matrix composites have a wide range of applications, involving many types of components and complex shapes. Combined with the characteristics of the ceramic matrix composite material forming process, it is difficult to integrally form some ceramic matrix composite material components with relatively complex structures. [0003] The existing prepreg co-curing molding process is mostly used in the molding of resi...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): C04B35/80C04B35/565C04B35/65C04B35/622C04B38/00
CPCC04B35/806C04B35/573C04B35/622C04B38/00C04B2235/656C04B2235/48
Inventor 姜卓钰焦健杨金华吕晓旭周怡然
Owner AVIC BEIJING INST OF AERONAUTICAL MATERIALS
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