Ceramic-matrix composites

Trefilov, V. I.

doi:10.1007/978-94-011-1280-2_1

Cited by 4 publications

(4 citation statements)

References 72 publications

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“…The graphitization process that thermally transforms non-graphitic carbon materials into graphite is well known in the carbon matrix composites. To be successful, several parameters must be properly conceived and tailored during the process, such as constituent composition and configuration, presence of impurities, atmosphere temperature and pressure, treatment duration, and so on [ 45 ]. The CVI process was selected as it allows us to manufacture high thermal conductivity products and because the process may result in a very pure and graphitizable carbon matrix [ 46 ].…”

Section: Methodsmentioning

confidence: 99%

Advanced Radar Absorbing Ceramic-Based Materials for Multifunctional Applications in Space Environment

et al. 2018

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In this review, some results of the experimental activity carried out by the authors on advanced composite materials for space applications are reported. Composites are widely employed in the aerospace industry thanks to their lightweight and advanced thermo-mechanical and electrical properties. A critical issue to tackle using engineered materials for space activities is providing two or more specific functionalities by means of single items/components. In this scenario, carbon-based composites are believed to be ideal candidates for the forthcoming development of aerospace research and space missions, since a widespread variety of multi-functional structures are allowed by employing these materials. The research results described here suggest that hybrid ceramic/polymeric structures could be employed as spacecraft-specific subsystems in order to ensure extreme temperature withstanding and electromagnetic shielding behavior simultaneously. The morphological and thermo-mechanical analysis of carbon/carbon (C/C) three-dimensional (3D) shell prototypes is reported; then, the microwave characterization of multilayered carbon-filled micro-/nano-composite panels is described. Finally, the possibility of combining the C/C bulk with a carbon-reinforced skin in a synergic arrangement is discussed, with the aid of numerical and experimental analyses.

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Section: Methodsmentioning

confidence: 99%

Advanced Radar Absorbing Ceramic-Based Materials for Multifunctional Applications in Space Environment

et al. 2018

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“…These manufacturing processes allowed for the creation of a denser matrix, allowing a relatively uniform distribution of separately coated filament fibers. In addition, new CMC material facilities have been established since 2019, producing SiC fiber CMC parts for jet engines and advanced ceramic coating made from oxide layers [246].…”

Section: Cmc Adoption Roadmapmentioning

confidence: 99%

Ceramic Matrix Composites for Aero Engine Applications—A Review

Karadimas

Salonitis

2023

Applied Sciences

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Ceramic matrix materials have attracted great attention from researchers and industry due to their material properties. When used in engineering systems, and especially in aero-engine applications, they can result in reduced weight, higher temperature capability, and/or reduced cooling needs, each of which increases efficiency. This is where high-temperature ceramics have made considerable progress, and ceramic matrix composites (CMCs) are in the foreground. CMCs are classified into non-oxide and oxide-based ones. Both families have material types that have a high potential for use in high-temperature propulsion applications. The oxide materials discussed will focus on alumina and aluminosilicate/mullite base material families, whereas for non-oxides, carbon, silicon carbide, titanium carbide, and tungsten carbide CMC material families will be discussed and analyzed. Typical oxide-based ones are composed of an oxide fiber and oxide matrix (Ox-Ox). Some of the most common oxide subcategories are alumina, beryllia, ceria, and zirconia ceramics. On the other hand, the largest number of non-oxides are technical ceramics that are classified as inorganic, non-metallic materials. The most well-known non-oxide subcategories are carbides, borides, nitrides, and silicides. These matrix composites are used, for example, in combustion liners of gas turbine engines and exhaust nozzles. Until now, a thorough study on the available oxide and non-oxide-based CMCs for such applications has not been presented. This paper will focus on assessing a literature survey of the available oxide and non-oxide ceramic matrix composite materials in terms of mechanical and thermal properties, as well as the classification and fabrication methods of those CMCs. The available manufacturing and fabrication processes are reviewed and compared. Finally, the paper presents a research and development roadmap for increasing the maturity of these materials allowing for the wider adoption of aero-engine applications.

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“…and matrix microstructure (orientation of graphitic planes and fibre/matrix interfaces): in turn, these latter features control the material properties. [1][2][3][4][7][8][9][10][11][12][13][14][15][16][17][18] In the present work, objective was to make two C f / C m composites, Type A and Type B through an economical route without employing costlier CVI process. These two composites had 2D fibre arrangements but different types and volumes of carbon fibre reinforcements.…”

Section: Step 3: Graphitisation Treatmentmentioning

confidence: 99%

Effect of carbon fabric type on properties of 2D carbon–carbon composites processed by liquid pitch impregnation–pyrolysis

Jana

Rajulapati

Prasad

et al. 2016

Journal of Composite Materials

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The present study reports on the microstructural, physical, thermal and mechanical properties of two types (A and B) of carbon-carbon composites processed by an economical route. Skeleton composites were first made by pyrolysing laminated carbon fibre-reinforced phenolic composites and subsequently densified by liquid pitch impregnation-pyrolysis process. Both types of composite employed polyacrylonitrile-based 8-harness satin woven carbon fabrics, Type A being woven with tows of continuous fibres, whereas Type B used yarns of discontinuous fibres. Experimental results indicated that the Type A composite had better flexural and tensile modulus and strength values. However, the Type B composite had better interlaminar shear strength and through-thickness thermal conductivity, despite being less dense. These results are discussed and explained from microstructural and fractographic analysis using optical and scanning electron microscopes. Finally, the results were compared with those intended for similar applications.

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Ceramic-matrix composites

Cited by 4 publications

References 72 publications

Advanced Radar Absorbing Ceramic-Based Materials for Multifunctional Applications in Space Environment

Advanced Radar Absorbing Ceramic-Based Materials for Multifunctional Applications in Space Environment

Ceramic Matrix Composites for Aero Engine Applications—A Review

Effect of carbon fabric type on properties of 2D carbon–carbon composites processed by liquid pitch impregnation–pyrolysis

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