The preparation and mechanical properties of carbon/carbon (C/C) composite and carbon fiber reinforced silicon carbide (Cf/SiC) composite joint by partial transient liquid phase (PTLP) diffusion bonding process

Wang, Jie; Yang, Guanzhong; Zhang, Fuqi; Xiong, Yi; Xiong, Qinglian

doi:10.1016/j.vacuum.2018.09.045

Cited by 21 publications

(3 citation statements)

References 20 publications

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“…The results of the EDS line scan in Figure 3 show that most of the Si elements are transferred to the C‐Al reaction interface layer during the impregnation of the alloy with the carbon matrix [35]. The elemental analysis in Figures 3b and 3c shows that aluminium carbide and silicon carbide are generated at the interface and the generation of silicon carbide significantly inhibits the generation of aluminium carbide.…”

Section: Resultsmentioning

confidence: 99%

Thermal shock resistance enhancement by improved interfacial bonding for carbon/aluminium composites

et al. 2022

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Carbon/aluminium (C/Al) composites have the advantages of low density and high electrical conductivity, which have potential applications in aerospace, rail transportation and other fields. However, the unstable bonding of the C/Al interface and significant thermal expansion differences have resulted in risks of the composites' failure once suffering from severe thermal shock. In this work, the C/Al composites were prepared by the pressure impregnation method, and silicon (Si) was added to overcome the problems of C/Al non‐wettability and thermal expansion differences. The effects of mass fractions of doped silicon on the mechanical properties, electrical conductivity and thermal shock resistance of C/Al composites were also examined. Results show that the formed SiC interlayer has effectively enhanced the interfacial bonding and reduced the differences in the thermal expansion coefficient of each component. As a result, the thermal shock resistance of the composites has been remarkably improved, and the flexural strength could remain 90% of the original level after the thermal shock test, compared with 50% of that without Si doping.

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Section: Resultsmentioning

confidence: 99%

Thermal shock resistance enhancement by improved interfacial bonding for carbon/aluminium composites

et al. 2022

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“…The oxidation and erosion resistance is enhanced due to the properties of the C/SiC composites. Additionally, the C/SiC composites can be used for lightweight and harsh applications, due to the fact that the density of the carbon is below the density of numerous metallic materials [65][66][67].…”

Section: Carbon-carbon Compositesmentioning

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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“…It can be observed that DB is widely used in joining alloys, composites, and ceramics [20][21][22]. Several studies have shown that the addition of interlayers during the DB process can further improve the welding quality with lower bonding temperatures and pressures [21,[23][24][25]. On the one hand, it can improve surface contact and promote atomic diffusion.…”

Section: Introductionmentioning

confidence: 99%

Dissimilar diffusion bonding behaviour of Ti₂AlNb alloy and TiBw/Ti64 composites using the Ti interlayer

Pan

Zhang

Zhou³

et al. 2021

Science and Technology of Welding and Joining

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The Ti 2 AlNb alloy and TiBw/Ti64 composites were successfully bonded using a Ti interlayer at 900°C-1050°C for 20-80 min. The interface of the joints showed a layered microstructure. Moreover, the width of the diffusion zone gradually increased from 30 to 58 µm owing to sufficient atomic diffusion and phase transition at higher bonding temperatures with longer bonding times. The elemental concentration gradients caused by atomic diffusion promoted the precipitation of the O phase (Zone I) and the growth of the lamellar α phase (Zone II). A well-bonded joint was obtained and showed the highest shear strength of 460.9 MPa. Microcracks emerged in the diffusion zone and propagated into the TiBw/Ti64 substrate during the shear test, and the fracture mechanism inside the composites was intergranular ductile fracture mode.

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The preparation and mechanical properties of carbon/carbon (C/C) composite and carbon fiber reinforced silicon carbide (Cf/SiC) composite joint by partial transient liquid phase (PTLP) diffusion bonding process

Cited by 21 publications

References 20 publications

Thermal shock resistance enhancement by improved interfacial bonding for carbon/aluminium composites

Thermal shock resistance enhancement by improved interfacial bonding for carbon/aluminium composites

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

Dissimilar diffusion bonding behaviour of Ti₂AlNb alloy and TiBw/Ti64 composites using the Ti interlayer

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The preparation and mechanical properties of carbon/carbon (C/C) composite and carbon fiber reinforced silicon carbide (Cf/SiC) composite joint by partial transient liquid phase (PTLP) diffusion bonding process

Cited by 21 publications

References 20 publications

Thermal shock resistance enhancement by improved interfacial bonding for carbon/aluminium composites

Thermal shock resistance enhancement by improved interfacial bonding for carbon/aluminium composites

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

Dissimilar diffusion bonding behaviour of Ti2AlNb alloy and TiBw/Ti64 composites using the Ti interlayer

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Dissimilar diffusion bonding behaviour of Ti₂AlNb alloy and TiBw/Ti64 composites using the Ti interlayer