Mechanical properties and microstructure characterization of spark plasma and conventional sintering of Al–SiC–TiC composites

Ghasali, Ehsan; Pakseresht, Amirhossein; Rahbari, Ali; Eslami-shahed, Hossein; Alizadeh, Mohammad; Ebadzadeh, Touradj

doi:10.1016/j.jallcom.2016.01.118

Cited by 92 publications

(26 citation statements)

References 33 publications

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“…The lower sintering time and temperature beside PM technique leads to enhanced properties of composite. The capabilities of SPS method for preparation of aluminum matrix composite with unique properties have been reported by researchers [16][17][18] .…”

Section: Resultsmentioning

confidence: 95%

Low Temperature Sintering of Aluminum-Zircon Metal Matrix Composite Prepared by Spark Plasma Sintering

et al. 2016

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Aluminum-15 wt. % zircon metal matrix composite was fabricated using spark plasma sintering method at the temperature of 450°C and holding time of 4 min. The bending strength of 284±21 MPa and microhardness of 171±14 Vickers were determined for produced composite. XRD investigations proved that almost no decomposition of zircon particles as reinforcement occurred. SEM studies revealed the homogenous dispersion of reinforcement particles in the aluminum matrix.

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Section: Resultsmentioning

confidence: 95%

Low Temperature Sintering of Aluminum-Zircon Metal Matrix Composite Prepared by Spark Plasma Sintering

et al. 2016

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“…In this case, when the particles present agglomeration and the composite materials are assesed for sintering, there are possibilities to appear and to retain porosities, which can lead to unappropriated mechanical properties [53,54]. From the sintering method point of view, a spark plasma sintering process based on using aluminum matrix composites has proper behavior when developing adequate dense composites which also possess suitable mechanical properties, in comparison to conventional sintering methods [55,56].…”

Section: Ultra-high Temperature Ceramicsmentioning

confidence: 99%

Ceramic Composite Materials Obtained by Electron-Beam Physical Vapor Deposition Used as Thermal Barriers in the Aerospace Industry

et al. 2020

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This paper is focused on the basic properties of ceramic composite materials used as thermal barrier coatings in the aerospace industry like SiC, ZrC, ZrB 2 etc., and summarizes some principal properties for thermal barrier coatings. Although the aerospace industry is mainly based on metallic materials, a more attractive approach is represented by ceramic materials that are often more resistant to corrosion, oxidation and wear having at the same time suitable thermal properties. It is known that the space environment presents extreme conditions that challenge aerospace scientists, but simultaneously, presents opportunities to produce materials that behave almost ideally in this environment. Used even today, metal-matrix composites (MMCs) have been developed since the beginning of the space era due to their high specific stiffness and low thermal expansion coefficient. These types of composites possess properties such as high-temperature resistance and high strength, and those potential benefits led to the use of MMCs for supreme space system requirements in the late 1980s. Electron beam physical vapor deposition (EB-PVD) is the technology that helps to obtain the composite materials that ultimately have optimal properties for the space environment, and ceramics that broadly meet the requirements for the space industry can be silicon carbide that has been developed as a standard material very quickly, possessing many advantages. One of the most promising ceramics for ultrahigh temperature applications could be zirconium carbide (ZrC) because of its remarkable properties and the competence to form unwilling oxide scales at high temperatures, but at the same time it is known that no material can have all the ideal properties. Another promising material in coating for components used for ultra-high temperature applications as thermal protection systems is zirconium diboride (ZrB 2 ), due to its high melting point, high thermal conductivities, and relatively low density. Some composite ceramic materials like carbon-carbon fiber reinforced SiC, SiC-SiC, ZrC-SiC, ZrB 2 -SiC, etc., possessing low thermal conductivities have been used as thermal barrier coating (TBC) materials to increase turbine inlet temperatures since the 1960s. With increasing engine efficiency, they can reduce metal surface temperatures and prolong the lifetime of the hot sections of aero-engines and land-based turbines.

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“…Al 2 O 3 , SiC, TiC and zircon) have been added to aluminum matrix in order to overcome its low tensile strength and attain better hardness and tolerate high temperatures [12][13][14][15][16] . Zircon is a ceramic with high chemical stability, corrosion resistance and excellent thermal shock resistance.…”

Section: Introductionmentioning

confidence: 99%

Effect of Heating Method on Microstructure and Mechanical Properties of Zircon Reinforced Aluminum Composites

et al. 2016

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The mechanical properties and microstructure of aluminum matrix composites containing of zircon (10, 15 and 20 wt.%) as a reinforcement particles and cobalt additive (1, 1.5 and 2 wt.%) were investigated. The aluminum matrix composites were prepared by powder metallurgy technique and sintered in both conventional and microwave furnaces at temperatures higher than the melting point of aluminum. The results revealed that the density and mechanical strength of aluminum were increased by introducing zircon and cobalt particles. The maximum strength was obtained by adding 10 wt.% zircon sintered in microwave furnace at 950°C. The phase analysis and scanning electron microscopy of sintered composites were examined and found some interesting data about intermetallic compounds.

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Mechanical properties and microstructure characterization of spark plasma and conventional sintering of Al–SiC–TiC composites

Cited by 92 publications

References 33 publications

Low Temperature Sintering of Aluminum-Zircon Metal Matrix Composite Prepared by Spark Plasma Sintering

Low Temperature Sintering of Aluminum-Zircon Metal Matrix Composite Prepared by Spark Plasma Sintering

Ceramic Composite Materials Obtained by Electron-Beam Physical Vapor Deposition Used as Thermal Barriers in the Aerospace Industry

Effect of Heating Method on Microstructure and Mechanical Properties of Zircon Reinforced Aluminum Composites

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