Influence of the Architecture and Elemental-Chemical Composition on the Structure and Properties of Carbonaceous Composite Materials

Terentieva, V. S.; Лейпунский, И. О.; Eremina, A.I.; Астапов, А. Н.

doi:10.1615/compmechcomputapplintj.v2.i3.60

Cited by 5 publications

(3 citation statements)

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“…There are several lines of protection, such as inhibition of composite material matrices by antioxidants [1][2][3][4] or deposition of heat-resistant coatings onto the reinforcing fibers [5][6][7][8]. However, deposition of coatings onto the work surfaces of parts contacting with oxidizing media [9][10][11][12][13][14][15][16][17][18][19][20][21][22] seems to be the most efficient.…”

Section: Introductionmentioning

confidence: 99%

Investigation of Destruction Mechanisms for Heat-Resistant Coatings in Hypersonic Flows of Air Plasma

Астапов¹,

Rabinskiy²

2017

SSP

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The authors present the results of investigations of degradation processes that occur in the structure of heat-resistant coating of the Si-TiSi2-MoSi2-B-Y system in hypersonic flows of air plasma. It is found that coating operating capacity at surface temperatures Tw ≤ 1820÷1830°C is provided by the structural-phase state of its microcomposite main layer and formation on the coating surface of a heterogeneous passivating protective film. It is based on borosilicate glass reinforced by rutile microneedles. The mechanism of coating destruction at Tw ≥ 1850÷1860°C is erosion loss of oxide film as well as generation and growth of gas-filled cavities at the "coating main layer–oxide film" interface. As the pressure of saturated vapor of gaseous oxidation products (SiO, CO, MoO3 and B2O3) exceeds that of the ambient, the oxide film integrity is disrupted and oxidation process becomes active. The rates of erosion loss and sublimation grow as operating temperature increases and ambient pressure decreases.

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Section: Introductionmentioning

confidence: 99%

Investigation of Destruction Mechanisms for Heat-Resistant Coatings in Hypersonic Flows of Air Plasma

Астапов¹,

Rabinskiy²

2017

SSP

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“…Carbon-carbon composite materials (CCCM) are the basis for the creation of aerospace products that are operated under supercritical thermal, mechanical, and aerogasodynamic loads (Jin et al, 2018;Terentieva et al, 2011;Astapov and Terentieva, 2016;Yurishcheva et al, 2018). The main task in the technology of super-temperature carbon materials is to provide effective protection against oxidation under conditions of high-velocity flow around high-enthalpy flows of oxygen-containing gases (Astapov and Rabinskiy, 2017;Terentieva and Astapov, 2018;Astapov et al, 2019a;Astapov et al, 2019b).…”

Section: Introductionmentioning

confidence: 99%

CCCM Specific Surface Estimation in Process of Low-Temperature Oxidation

Pogodin¹,

Астапов²,

Rabinskiy³

2020

PTQ

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The low-temperature oxidation process of carbon-carbon composite materials (CCCM) with a pyrocarbon matrix has been examined. Oxidation at temperatures of 450 to 700 °C is characterized by internal burnout of the carbon phase without a noticeable change in the experimental samples external volume. Oxidation resistance analysis of CCCM structural components was performed. CCCM and carbon fibers specific surface area were estimated by the low-temperature adsorption of nitrogen and krypton using the Brunauer-Emmett-Teller model and the theory of density functional model. Pore size distribution was calculated by the semi-empirical Horvath-Kawazoe method. A significant increase (about 10-15 times) in specific surface area of the composite material, together with a rise in free volume ~5%, was accompanied by total weight loss of about 5%. Specific surface area changes occur as a result of anisotropic etching of carbon fibers surface with the formation of micropores with 0.5–2.0 nm diameter range. Although macropores are formed mainly due to the oxidation of thermosetting binder pyrolysis residue, they do not contribute to the specific surface increase but solely provide access to micropores. Microporosity evolution leads to an increase of structural discontinuity degree and, ultimately, to the loss of matrix-filler contact boundary. As a result, an overall weakening of material mechanical characteristics is to be noted. Thus, oxidative degradation is closely related to the increase in void space. A follow-up study is on-going. In fact, an open question remains, namely whether the oxidative process occurs differently in the micropores of diameter less than 2 nm and how it may contribute to the oxidative stress resistance behavior of CCCM.

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“…However, in oxygen-containing environments, the use of CCM is limited by the tendency of carbon and silicon carbide to oxidize at temperatures of about 400 and 1200 °C, respectively [1,[5][6][7][8], which leads to deterioration of their properties [6,[9][10]. Protection of structural materials from high-temperature oxidation and erosion can significantly extend the temperature intervals of their application, and in most cases is the only possible way to implement their functional and heatresistant properties.…”

Section: Introductionmentioning

confidence: 99%

High Temperature Coatings for Oxidation and Erosion Protection of Heat-Resistant Carbonaceous Materials in High-Speed Flows

Yurishcheva

Астапов

Lifanov

et al. 2018

KEM

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Modern approaches to the creation of single-layer and multi-layer high-temperature coatings for the protection of heat-resistant carbon-containing composite materials from oxidation and erosion in the high-speed fluxes of oxygen-containing gases are analyzed. Particularly have been outlined the heat-resistant coatings, the main components of which are either super refractory transition metal borides (ZrB2, HfB2, TiB2) with the addition of carbides (SiC, ZrC, HfC, TiC, TaC), silicides (MoSi2, TiSi2, ZrSi2, TaSi2, WSi2) and nitrides (HfN, ZrN, TiN), or refractory oxides (HfO2, ZrO2), or more complex synthetic compositions based on oxide ceramics. The results of fire gas-dynamic tests of coatings of perspective compositions are presented. The potential architecture of ultra-high-temperature coatings with high efficiency of protective action is justified.

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Influence of the Architecture and Elemental-Chemical Composition on the Structure and Properties of Carbonaceous Composite Materials

Cited by 5 publications

References 0 publications

Investigation of Destruction Mechanisms for Heat-Resistant Coatings in Hypersonic Flows of Air Plasma

Investigation of Destruction Mechanisms for Heat-Resistant Coatings in Hypersonic Flows of Air Plasma

CCCM Specific Surface Estimation in Process of Low-Temperature Oxidation

High Temperature Coatings for Oxidation and Erosion Protection of Heat-Resistant Carbonaceous Materials in High-Speed Flows

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