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A ceramic matrix hybrid composite material and its structure

A composite material and ceramic-based technology, applied in the field of ceramic-based hybrid composite materials and their structures, can solve the problems of thermal stability and high temperature oxidation resistance that cannot meet the requirements, and achieve light weight, good stability and long service life. Effect

Active Publication Date: 2016-01-27
TAICANG PAIOU TECH CONSULTING SERVICE
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

However, when these materials are used as materials for hot end parts, due to the existence of multiple phases, thermal stability and high temperature oxidation resistance cannot meet the requirements.

Method used

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  • A ceramic matrix hybrid composite material and its structure

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Effect test

Embodiment 1

[0014] A ceramic matrix hybrid composite material and its structure, the material is composed of four layers of different materials, namely nickel coating, SiC foam, SiC-densified carbon fiber prefabricated body and SiC coating. They are bonded to each other by interatomic forces to form a tubular structure. The nickel coating is on the outermost layer of the tubular structure, attached to the SiC foam surface, with a thickness of 0.8mm. SiC foam and SiC-densified carbon fiber preform constitute the main body of the tubular structure, with thicknesses of 4 mm and 1 mm, respectively. The SiC coating is located on the inner surface of the SiC tube and is the innermost layer of the tubular structure with a thickness of 0.2mm.

Embodiment 2

[0016] A ceramic-based hybrid composite material and its structure, the material is composed of four layers of different materials, namely nickel coating, SiC foam, SiC-densified carbon fiber prefabricated body tube and SiC coating. They are bonded to each other by interatomic forces to form a tubular structure. The nickel coating is located on the outermost layer of the tubular structure, attached to the surface of the SiC foam, with a thickness of 0.6mm. SiC foam and SiC-densified carbon fiber preform constitute the main body of the tubular structure, with thicknesses of 5 mm and 2 mm, respectively. The SiC coating is located on the inner surface of the SiC tube and is the innermost layer of the tubular structure with a thickness of 0.5mm.

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Abstract

The invention discloses a ceramic matrix hybrid composite material and a structure thereof. The material adopts a multi-layer structure, is tubular and comprises a nickel coating, SiC foam, a SiC-thickened carbon fiber preform and a SiC coating from outside to inside sequentially. Thicknesses of the nickel coating, the SiC foam, the SiC-thickened carbon fiber preform and the SiC coating are 0.5-3 mm, 1-5 mm, 0.5-5 mm and 0.1-0.5 mm respectively. The nickel coating, the SiC foam, the SiC-thickened carbon fiber preform and the SiC coating are bonded mutually through inter-atom acting force, can work stably in a high-temperature environment, is oxidation-resistant and anti-corrosion and can be used as a demanding high-temperature structural part such as an aerospace vehicle spray pipe.

Description

technical field [0001] The invention relates to a composite material and its structure, in particular to a ceramic matrix hybrid composite material and its structure. Background technique [0002] High-performance power is the basis for the development of advanced aviation and spacecraft. Improving the thrust-to-weight ratio of aero-engines and the impulse-to-mass ratio of rocket engines is the only way to improve the performance of advanced aviation and spacecraft. All of these require the continuous reduction of engine structural weight and Improve the temperature resistance of engine components. Therefore, the development of new ultra-high temperature composite materials with high temperature resistance and low density to replace superalloys and refractory metal materials has become the key and foundation for the development of high-performance engines. It is generally believed internationally that SiC ceramic matrix composites are one of the technical commanding heights...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B32B1/08B32B15/04B32B18/00B32B33/00
Inventor 陈照峰聂丽丽
Owner TAICANG PAIOU TECH CONSULTING SERVICE