Advances in oxidation and ablation resistance of high and ultra-high temperature ceramics modified or coated carbon/carbon composites

Jin, Xiaochao; Lu, Chunsheng; Wang, Zhihui

doi:10.1016/j.jeurceramsoc.2017.08.013

Cited by 301 publications

(73 citation statements)

References 240 publications

Supporting

Mentioning

Contrasting

Unclassified

Order By: Relevance

“…Refractory compounds of transitional metals (Ta, Nb, Ti, Zr, Hf) usually serve as the basis for UHTCs [5]. Potential applications of UHTCs include hightemperature solar concentrators for renewable energy industry, barrier coatings, hard coatings [6][7][8][9]. TaC (Tm=3950°С) and ZrC (Tm=3420 °С) are among the most refractory compounds known today [10][11][12].…”

Section: Introductionmentioning

confidence: 99%

Ab-initio modeling and experimental investigation of properties of ultra-high temperature solid solutions TaxZr1-xC

Vorotilo

Sidnov

Mosyagin

et al. 2019

Journal of Alloys and Compounds

View full text Add to dashboard Cite

Due to their high melting temperature, high-temperature oxidation resistance and outstanding mechanical properties, solid solutions TaxZr1-xC are a promising ultra-high temperature ceramic (UHTC). However, the accelerated knowledge-based development of UHTCs solid solutions requires reliable data regarding the properties of the solution phases in the whole interval of concentrations. In particular, there are contradictory reports regarding the existence of the miscibility gap in Ta-Zr-C system at the temperatures below 900 o С. In this work, we carry out the ab-initio calculation of the thermodynamic properties of TaxZr1-xC alloys and demonstrate that the decomposition of the solid solutions into TaC and ZrC should not occur. We synthesize single-phase specimens with the composition TaxZr1-xC (x=0.9, 0.8, 0.6, 0.3) by self-propagating hightemperature synthesis (SHS) and anneal it for 40 hours. We do not observe any sign of the decomposition of the solid solution during the annealing, corroborating the conclusions obtained in theoretical simulations.

show abstract

Section: Introductionmentioning

confidence: 99%

Ab-initio modeling and experimental investigation of properties of ultra-high temperature solid solutions TaxZr1-xC

Vorotilo

Sidnov

Mosyagin

et al. 2019

Journal of Alloys and Compounds

View full text Add to dashboard Cite

show abstract

“…Another class of materials that have applications in the aerospace industry is represented by the ultra-high temperature ceramics. These materials are described as possessing a blend of properties that are characterized by very good and suitable mechanical properties and at the same time a significant meting point, which can reach up to 3000 °C and even exceed this value [13,21]. Metallic composites are manufactured by reinforcing various types of metal matrices, such as titanium, aluminum, copper, magnesium, etc.…”

Section: Figurementioning

confidence: 99%

“…These ceramics exhibit a superior combination of properties characterized by high melting points together with mechanical properties. In this sense, the use of ultra-high temperature ceramics in extreme environments make them excellent potential candidate for these applications [13].…”

Section: Ultra-high Temperature Ceramicsmentioning

confidence: 99%

“…When it comes to temperatures that can be reached in this field, the aerospace industry has an ultrahigh temperature class that is generally placed from 1600 • C and can reach up to 2200 • C [13]. These temperatures require the use of materials that can withstand very high temperatures and also have exclusive mechanical properties [14,15].…”

Section: Introductionmentioning

confidence: 99%

See 1 more Smart Citation

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

et al. 2020

View full text Add to dashboard Cite

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.

show abstract

“…), ouyangsust@126.com (Ouyang H.B. ) ACCEPTED MANUSCRIPT (C/C-UHTCs) composites present a promising application as high temperature structural components for space vehicles, such as nose tips, leading edges, and nozzles, due to their excellent high temperature mechanical properties, good thermal shock resistance and ablation resistance [1,2]. To date, various techniques have been used to prepare the C/C-UHTCs composites, such as precursor infiltration and pyrolysis (PIP) process [3], reactive melt infiltration (RMI) [4,5], solution infiltration [6,7], and powder slurry infiltration [8,9].…”

Section: Introductionmentioning

confidence: 99%

Microstructure and properties of C/C–ZrC composites prepared by hydrothermal deposition combined with carbothermal reduction

Ouyang

et al. 2018

Journal of Alloys and Compounds

View full text Add to dashboard Cite

Carbon fiber reinforced carbon matrix containing ZrC (C/C-ZrC) composites were prepared by hydrothermal deposition combined with carbothermal reduction. The submicron ZrC particles (100~300 nm) were dispersed in the matrix. The stress-strain curves of the composites presented a typical pseudo-plastic fracture behavior. The mass and linear ablation rates of the composites were 3.7×10-3 g/s and 4.2×10-3 mm/s, respectively. The formation of ZrO 2 glass layer reduced erosion of the composites in the ablation center. The continuous C-ZrC-ZrO 2 skeleton layer generated from the oxidation of ZrC can protect the composites from erosion at the ablation brim region. The obtained C/C-ZrC composites present a promising potential as ablation resistance materials.

show abstract

Advances in oxidation and ablation resistance of high and ultra-high temperature ceramics modified or coated carbon/carbon composites

Cited by 301 publications

References 240 publications

Ab-initio modeling and experimental investigation of properties of ultra-high temperature solid solutions TaxZr1-xC

Ab-initio modeling and experimental investigation of properties of ultra-high temperature solid solutions TaxZr1-xC

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

Microstructure and properties of C/C–ZrC composites prepared by hydrothermal deposition combined with carbothermal reduction

Contact Info

Product

Resources

About