Effects of ablation at different regions in three-dimensional orthogonal C/SiC composites ablated by oxyacetylene torch at 1800°C

Yan, Bo; Chen, Zhaofeng; Zhu, Jianxun; Zhang, Jianzhong; Jiang, Yun

doi:10.1016/j.jmatprotec.2008.08.002

Cited by 35 publications

(14 citation statements)

References 21 publications

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“…Mei et al firstly analyzed behavior of 2‐dimensional C/SiC composites subjected to thermal cycling in controlled environments. Chen et al investigated the microstructure and ablation properties of 2‐dimensional, 2.5‐dimensional, and 3‐dimensional C/SiC composites by oxy‐acetylene flame with different temperature, respectively. It is shown that thermal decomposition and oxidation of SiC matrix were the main ablation behavior at relative lower temperature, while subliming of carbon fiber and silicon carbide matrix was the main ablation behavior at relative higher temperature.…”

Section: Introductionmentioning

confidence: 99%

Microstructure Evolution and Ablation Mechanism of C/C and C/C‐SiC Composites Under a Hypersonic Flowing Propane Torch

Jin

Jiang

Wang³

2017

Adv Eng Mater

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The high-velocity oxygen fuel thermal spray system can provide a hypersonic flowing environment in which the temperature, pressure, and speed are all sufficiently high to represent a more realistic environment of hypersonic vehicles than that produced by traditional oxyacetylene flame. In this work, the ablation resistance of C/C and C/C-SiC composites under hypersonic flowing propane flame is investigated, and the microstructure evolution during the ablation process is examined. It is found that different ablation regions are formed depending on the size, and the distributions of temperature and pressure on the front surface of the samples. With the increase of ablation time, a dense and continuous oxide layer forms, which acts as a barrier to prevent the interaction of oxidizing gases and composites, and can also block the conducted heat and resist high temperature scouring of hypersonic flowing flame. In addition, a numerical analysis is performed using ANSYS Fluent software to investigate the fields of velocity, pressure, and temperature on the front surface and around the carbon fibers of the sample. The simulation results further demonstrate the evolution of microstructures of C/C and C/C-SiC composites.

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Section: Introductionmentioning

confidence: 99%

Microstructure Evolution and Ablation Mechanism of C/C and C/C‐SiC Composites Under a Hypersonic Flowing Propane Torch

Jin

Jiang

Wang³

2017

Adv Eng Mater

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“…However, in addition to their relatively high cost, one of the major problems of the CMC/carbon based protection systems is their poor oxidative behavior: under exposure to a hot oxidative gas, a notable bulk material mass loss is observed due to chemical reactions with oxygen and water vapour. These phenomena have been reported by many authors [6][7][8][9][10] and more reliable carbon based systems have been searched for.…”

Section: Introductionmentioning

confidence: 72%

“…For short exposure time of SiRC, mass measurements provide evidence for this hypothesis while for longer exposure, the heat and oxygen species released by oxyacetylene torch diffuse through the composite and the active oxidation begins (exposure time > 5 s). The reaction 2SiC 3O 2SiO 2CO    below shows the SiO 2 formation [4,8,10]: produce liquid SiO 2 in impacted area. Voids appear in the resulting volume (volumetric ablation).…”

Section: Differences In Ablation Resistance Between Sirc and Crcmentioning

confidence: 99%

Ablation Properties of C Fibers and SiC Fibers Reinforced Glass Ceramic Matrix Composites Upon Oxyacetylene Torch Exposure

Beaudet

Cormier²,

Dragon³

et al. 2011

MSA

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The ablation properties of two laminated composites, having both a glass ceramic matrix and different kinds of fibers (C or SiC) with the same architecture, are evaluated and compared. Ablation tests are performed using an oxyacetylene torch on samples having two different thicknesses. Mass loss and ablation depth are measured after flame exposure. The results obtained show that the decomposition of SiC fibers during thermal exposure has a significant impact on ablation behavior. Oxidation of SiC produces a liquid SiO<sub>2</sub> film at the top of the material during ablation. This leads to an improved ablation resistance compared to the glass ceramic matrix/C composite, especially in case of successive flame exposures where the SiO<sub>2</sub> film consumes a substantial fraction of the heat flow during its liquefaction upon re-heating

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“…The hems of the microcracks are more easily oxidised due to their high specific surface area to thermal oxidising atmosphere. 23 The Si 3 N 4 fragments were eroded and oxidised by the high speed airflow to form SiO 2 and adhere to the residual part. After ablation, the residual Si 3 N 4 particles were covered by the solidified SiO 2 glass film, which led to the amber-like microstructure.…”

Section: Microscopic Characterisationmentioning

confidence: 99%

Morphology and ablation mechanism of C_f/Si₃N₄composites ablated by oxyacetylene torch at 2200°C

Chen

Wan

Fang

et al. 2011

Corrosion Engineering, Science and Technology

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Si 3 N 4 ceramic matrix composites reinforced by carbon fibres (C f /Si 3 N 4 ) were prepared by low pressure chemical vapour infiltration at 1250uC using SiCl 4 and NH 3 as precursor. The as prepared C f /Si 3 N 4 composites were ablated to determine the mechanism of the ablation resistance and oxidisation resistance by oxyacetylene torch at 2200uC. The morphology and microstructure of the composites were examined by scanning electron microscopy. The phase compositions of the composites were confirmed by energy dispersive X-ray spectroscopy and Xray diffraction. The results indicated that the matrix of the C f /Si 3 N 4 composites was composed of the amorphous Si 3 N 4 and nanometre a-Si 3 N 4 . A central ablation region and a ring oxidisation region appeared on the surface of the as ablated C f /Si 3 N 4 composites. Sublimation of the Si 3 N 4 matrix and oxidation of the carbon fibres are the main ablation behaviours in the central region. Oxidation of the Si 3 N 4 matrix and deposition of SiO 2 particles are the main ablation behaviour in the ring region. A large number of SiO 2 liquid droplets produced during ablation were retained and formed spherical solid particles on the surface of the ring region after ablation. For the mismatch of the coefficient of thermal expansion of the carbon fibres and the Si 3 N 4 matrix, Si 3 N 4 matrix was cracked under the thermal impact of the oxyacetylene flame. With the passive oxidation of the as cracked surface, the continuous SiO 2 liquid was formed in the ring region. Subsequently, some residual Si 3 N 4 particles were covered by transparent SiO 2 layer to form an amber-like microstructure.

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Effects of ablation at different regions in three-dimensional orthogonal C/SiC composites ablated by oxyacetylene torch at 1800°C

Cited by 35 publications

References 21 publications

Microstructure Evolution and Ablation Mechanism of C/C and C/C‐SiC Composites Under a Hypersonic Flowing Propane Torch

Microstructure Evolution and Ablation Mechanism of C/C and C/C‐SiC Composites Under a Hypersonic Flowing Propane Torch

Ablation Properties of C Fibers and SiC Fibers Reinforced Glass Ceramic Matrix Composites Upon Oxyacetylene Torch Exposure

Morphology and ablation mechanism of C_f/Si₃N₄composites ablated by oxyacetylene torch at 2200°C

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Effects of ablation at different regions in three-dimensional orthogonal C/SiC composites ablated by oxyacetylene torch at 1800°C

Cited by 35 publications

References 21 publications

Microstructure Evolution and Ablation Mechanism of C/C and C/C‐SiC Composites Under a Hypersonic Flowing Propane Torch

Microstructure Evolution and Ablation Mechanism of C/C and C/C‐SiC Composites Under a Hypersonic Flowing Propane Torch

Ablation Properties of C Fibers and SiC Fibers Reinforced Glass Ceramic Matrix Composites Upon Oxyacetylene Torch Exposure

Morphology and ablation mechanism of Cf/Si3N4composites ablated by oxyacetylene torch at 2200°C

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Morphology and ablation mechanism of C_f/Si₃N₄composites ablated by oxyacetylene torch at 2200°C