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A preparation method of continuous fiber reinforced thermal structural material composite interface layer

A technology of continuous fiber and thermal structure, which is applied in the field of preparation of composite interface layer of continuous fiber reinforced thermal structural material, can solve the problems of loss of fiber reinforcement and toughening effect, brittle failure of continuous fiber reinforced thermal structural composite material, etc. Performance, improved mechanical properties and high temperature stability, long service life at high temperature

Active Publication Date: 2018-05-01
BEIHANG UNIV
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

[0005] The purpose of the present invention is to provide a method for preparing the interface of continuous fiber-reinforced thermal structural composite materials, aiming to solve the problem that oxide fibers tend to form a strong bonding interface with oxide ceramic matrix during high-temperature molding and use, resulting in the Brittle failure of continuous fiber-reinforced thermal structural composites with strong bonding interface, loss of reinforcement and toughening effect of fibers

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  • A preparation method of continuous fiber reinforced thermal structural material composite interface layer
  • A preparation method of continuous fiber reinforced thermal structural material composite interface layer

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specific Embodiment 1

[0031] Such as figure 1 As shown, the embodiment of the present invention provides a method for preparing an interface layer of a continuous fiber reinforced thermal structural composite material, including:

[0032] Step S101, using oxide fibers as raw materials to obtain oxide fiber preforms;

[0033] Step S102, preparing a cracked carbon layer on the surface of the oxide fiber preform;

[0034] Step S103, preparing a zirconia layer on the surface of the oxide fiber preform.

[0035] In the embodiment of the present invention, a cracked carbon layer and a zirconia layer are prepared on the surface of the oxide fiber preform as an interface layer. After the cracked carbon layer is oxidized, a porous interface can be formed, and a layer of zirconia layer is added on the cracked carbon layer. , forming a composite interface layer of cracked carbon and zirconia, which can prevent the infiltration of oxygen and prevent excessive oxidation of the carbon layer. The introduction o...

specific Embodiment 2

[0049] The embodiment of the present invention provides a preparation method of an alumina fiber prefabricated body reinforced alumina ceramic matrix composite material interface layer, which specifically includes the following process steps:

[0050] (1) Preparation of fiber prefabricated body: alumina fiber is used as raw material, and alumina fiber prefabricated body is prepared by weaving process; alumina fiber prefabricated body is three-dimensional four-way structure, three-dimensional five-way structure, three-dimensional six-way structure or three-dimensional orthogonal Equal structure; the fiber volume fraction in the alumina fiber preform is 40% to 45%.

[0051] (2) Pretreatment of alumina fiber preforms: put the alumina fiber preforms in step (1) into a muffle furnace, and heat up to 500°C to 500°C in an air atmosphere at a rate of 5°C / min to 10°C / min Keep warm at 600°C for 1-2 hours, then cool naturally to below 100°C and take out.

[0052] (3) Preparation of carb...

specific Embodiment 3

[0055] The embodiment of the present invention provides a preparation method of an alumina fiber prefabricated body reinforced alumina ceramic matrix composite material interface layer, which specifically includes the following process steps:

[0056] (1) Preparation of fiber prefabricated body: Alumina fiber preformed body with three-dimensional and four-directional structure was prepared by weaving process with alumina fiber as raw material, and the volume fraction of alumina fiber preformed body was controlled to be 40%.

[0057] (2) Pretreatment of alumina fiber preforms: put the alumina fiber preforms in step (1) into a muffle furnace, heat up to 500°C at 5°C / min in an air atmosphere, keep warm for 2h, and cool naturally Take it out below 100°C.

[0058] (3) Preparation of carbon interface: Utilize chemical vapor deposition process to prepare cracked carbon layer on the surface of alumina fiber preform obtained in above step (2); chemical vapor deposition process paramete...

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Abstract

The present invention provides a continuous fiber reinforced thermal structure composite material interface layer preparation method. According to the present invention, a weak bonding interface between a cracking carbon layer and a zirconium oxide layer and having sufficient damage tolerance is provided between continuous fibers and an oxide substrate, and when the substrate crack expands along the interface, the fiber and the substrate interface material can be debonded so as to be stripped out so as to achieve the toughening purpose, such that the problem of the substrate and the fiber are subjected to the reaction to form the excessively strong bonding surface so as to cause the brittle fracture of the composite material can be solved; and the invention provides a ceramic-based composite material composite interface layer preparation method, wherein the mechanical property and the high temperature stability of the thermal structure material having the composite interface layer are improved, and the high temperature service life is long by using the thermal structure material having the composite interface layer in the aeroengine thermal end part.

Description

technical field [0001] The invention relates to the technical field of interface design of composite materials, in particular to a method for preparing a composite interface layer of a continuous fiber reinforced thermal structural material. Background technique [0002] With the development of a new generation of aircraft in the aerospace field, the development and application of advanced ceramic matrix composites are becoming more and more important. At present, in order to improve the performance of the engine, materials are required to have the characteristics of high temperature resistance, high strength, high toughness and environmental stability, and ceramic matrix composites provide the possibility for its realization. Ceramic materials such as SiC and alumina have a series of advantages such as high temperature resistance and low density, so they have attracted people's attention. SiC f The / SiC composite material has successfully passed the demonstration and veri...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): C04B35/80C04B35/84C04B41/89
CPCC04B35/803C04B41/009C04B41/52C04B41/89C04B2235/96C04B35/10C04B41/5001C04B41/4531C04B41/5042C04B41/4537
Inventor 罗瑞盈王天颖
Owner BEIHANG UNIV