High-temperature-resistant ceramic-based composite member and connecting method thereof

A composite material component and high temperature resistant ceramic technology, applied in the field of ceramic matrix composite materials, can solve the problems of connection position failure and low connection strength, and achieve the effects of reducing brittle fracture, improving mechanical strength, and improving the degree of thermal matching.

Active Publication Date: 2019-03-19
AEROSPACE INST OF ADVANCED MATERIALS & PROCESSING TECH
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Chinese patent application 201611182773.1 discloses a SiC ceramic matrix composite component and its preparation method. Although the preparation method improves the connection strength of the joint of the component compared with the traditional C/SiC composite component preparation method, the connection Because the connection strength is still low, the method is only suitable for the connection of carbon fiber reinforced carbon ceramic matrix composites (C/C ceramic matrix composites), C/SiC ceramic matrix composites, etc.
The existing connection methods are suitable for

Method used

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Examples

Experimental program
Comparison scheme
Effect test

Embodiment 1

[0055] ① Choose a density of 0.48g / cm 3 The needle-punched carbon fiber preform was placed in a high-temperature furnace, and under the protection of argon, the temperature was 1800° C. for 1 hour.

[0056] ② Vapor deposition of carbon on carbon fiber preforms: place the high-temperature treated carbon fiber preforms in a chemical vapor deposition furnace, the deposition gas is propane, the deposition temperature is 920°C, and the carbon fiber preforms are deposited to a density of 0.86g / cm 3 , to get the prefab to be connected.

[0057] ③ Machining: The prefabricated parts to be connected in ② are machined into two flat prefabricated parts to be connected (the first prefabricated part to be connected and the second prefabricated part to be connected), and There are a plurality of rivet holes for rivet connection correspondingly and evenly spaced on the parts, and they are cleaned after the processing is completed.

[0058] ④ Mix Si powder with a particle size of 50nm, chopp...

Embodiment 2

[0065] ① Choose a density of 0.75g / cm 3 The punctured structure carbon fiber prefabricated body, and then the punctured structure prefabricated body was placed in a high temperature furnace, under the protection of argon, the temperature was 1700°C, and the high temperature treatment was carried out for 1h.

[0066] ② Vapor-deposited carbon on carbon fiber preforms: place the high-temperature-treated carbon fiber preforms in a chemical vapor deposition furnace, the deposition gas is propane, the deposition temperature is 1050°C, and the preforms are deposited to a density of 0.95g / cm 3 , to get the prefab to be connected.

[0067] ③ Machining: The prefabricated parts to be connected in ② are machined into two flat prefabricated parts to be connected (the first prefabricated part to be connected and the second prefabricated part to be connected), and There are a plurality of rivet holes for rivet connection correspondingly and evenly spaced on the parts, and they are cleaned a...

Embodiment 3

[0075] ① Choose a density of 0.42g / cm 3 The stitched structure carbon fiber preform and the density is 0.49g / cm 3 The needle-punched carbon fiber preform, and then high-temperature treatment for each carbon fiber preform: place the preform in a high-temperature furnace, under the protection of argon, at a temperature of 1800°C, and perform high-temperature treatment for 1 hour.

[0076] ②Vapor-deposited carbon on each carbon fiber preform: place the high-temperature-treated carbon fiber preform in a chemical vapor deposition furnace, the deposition gas is propane, the deposition temperature is 920°C, and the stitched structure preform is deposited to a density of 0.92g / cm 3 , acupuncture structure preform to a density of 0.91g / cm 3 , respectively get two prefabs to be connected.

[0077] ③ Machining: Machining the prefabricated part (the first prefabricated part to be connected) of the suture structure in ② into a flat plate shape, and machining the prefabricated part (the...

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Abstract

The invention relates to a high-temperature-resistant ceramic-based composite member and a connecting method thereof. The method comprises the following steps: (1) uniformly mixing silicon powder, chopped carbon fibers, an organic dispersing agent and a phenolic resin to obtain mixed slurry; (2) coating a joint face of a first to-be-connected prefabricated member and/or a second to-be-connected prefabricated member with the mixed slurry, and laminating and connecting the joint face of the first to-be-connected prefabricated member and the second to-be-connected prefabricated member so as to obtain a pre-connecting piece, wherein the first to-be-connected prefabricated member and/or the second to-be-connected prefabricated member are/is made from fiber preforms; (3) at least impregnating the joint of the pre-connecting piece with the mixed slurry, and sequentially curing and splitting the impregnated pre-connecting piece so as to obtain a pre-connected member; and (4) carrying out a silicon-zirconium alloy infiltration reaction on the pre-connected member, thereby obtaining the high-temperature-resistant ceramic-based composite member. The method disclosed by the invention has the advantages of being simple in process, capable of obviously enhancing the member connection strength and enabling the overall member to be high-temperature-resistant, and the like.

Description

technical field [0001] The invention belongs to the technical field of ceramic matrix composite materials, and in particular relates to a high-temperature-resistant ceramic matrix composite material component and a connection method thereof. Background technique [0002] With the development of aerospace technology and the development needs of future aircraft, lightweight, high-strength fiber-reinforced high-temperature structural composite materials have increasingly become key structural materials supporting the development of hypersonic aircraft and engines. For example, continuous carbon fiber toughened silicon carbide ceramic matrix composite (C / SiC ceramic matrix composite) is an ideal high-temperature structural material, which has a series of advantages such as high temperature resistance, low density, high strength, and thermal shock resistance. It is a thermal protection material developed earlier, with lower cost and more mature technology. In the practical appli...

Claims

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Application Information

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IPC IPC(8): C04B35/56C04B35/573C04B35/80C04B35/622
CPCC04B35/5622C04B35/573C04B35/622C04B35/806C04B2235/404C04B2235/428C04B2235/48C04B2235/5248C04B2235/616C04B2235/96
Inventor 金鑫王鹏左红军刘伟宋环君于艺于新民霍鹏飞
Owner AEROSPACE INST OF ADVANCED MATERIALS & PROCESSING TECH
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