SiC nanowire-toughened MoSi2-SiC coating to protect carbon/carbon composites against oxidation

To protect carbon/carbon (C/C) composites against oxidation, a SiC nanowire-toughened MoSi₂-SiC coating was prepared on them using a two-step technique of chemical vapor deposition and pack cementation. SiC nanowires obtained by chemical vapor deposition were distributed random-orientedly on C/C substrates and MoSi₂-SiC was filled in the holes of SiC nanowire layer to form a dense coating. After introduction of SiC nanowires, the size of the cracks in MoSi₂-SiC coating decreased from 18 ± 2.3 to 6 ± 1.7 μm, and the weight loss of the coated C/C samples decreased from 4.53% to 1.78% after oxidation in air at 1500 °C for 110 h.     

Microstructure and oxidation of multi-layer MoSi2-CrSi2-Si coatings for SiC coated carbon/carbon composites

Multi-layer MoSi₂-CrSi₂-Si anti-oxidation coatings with different compositional ratios were prepared on the surface of SiC coated carbon/carbon (C/C) composites by a two-step pack cementation method. The microstructure and anti-oxidation performance of the coating were studied. The results show that the multi-layered coatings could protect the C/C composites from oxidation in air at 1773 K for 1000 h or 1873 K for 750 h, respectively. The anti-oxidation performance of the multi-layer MoSi₂-CrSi₂-Si coating is mainly attributed to their dense and microcrack-free structure, appropriate thermal expansion coefficient and the well dispersed MoSi₂ and CrSi₂ in the coating.     

The oxidation behavior and mechanical properties of MoSi2–CrSi2–SiC–Si coated carbon/carbon composites in high-temperature oxidizing atmosphere

A MoSi₂–CrSi₂–SiC–Si multi-component coating was prepared on the surface of carbon/carbon (C/C) composites by a two-step pack cementation method. The microstructure, oxidation behavior and mechanical properties of the coating were studied. These results show that the multi-component coating could protect the C/C composites from oxidation in air at 1873 K for 300 h and withstand 30 thermal cycles between 1873 K and room temperature, respectively. The mass loss and mechanical property loss of the coated C/C composites are considered due to the worse fluidity of SiO₂ at intermediate temperatures and the thermal mismatch between the coating and C/C composites.     

A MoSi2/SiC oxidation protective coating for carbon/carbon composites

To protect carbon/carbon (C/C) composites against oxidation, a MoSi₂ outer coating was prepared on pack-cementation SiC coated C/C composites by a hydrothermal electrophoretic deposition. The phase composition, microstructure and oxidation resistance of the prepared MoSi₂/SiC coatings were investigated. Results show that hydrothermal electrophoretic deposition is an effective route to achieve crack-free MoSi₂ outer coatings. The MoSi₂/SiC coating can protect C/C composites from oxidation at 1773 K for 346 h with a weight loss of 2.49 mg cm⁻² and at 1903 K for 88 h with a weight loss of 5.68 mg cm⁻².     

Preparation and oxidation protection of CVD SiC/a-BC/SiC coatings for 3D C/SiC composites

An amorphous boron carbide (a-BC) coating was prepared by LPCVD process from BCl₃-CH₄-H₂-Ar system. XPS result showed that the boron concentration was 15.0 at.%, and carbon was 82.0 at.%. One third of boron was distributed to a bonding with carbon and 37.0 at.% was dissolved in graphite lattice. A multiple-layered structure of CVD SiC/a-BC/SiC was coated on 3D C/SiC composites. Oxidation tests were conducted at 700, 1000, and 1200 °C in 14 vol.% H₂O/8 vol.% O₂/78 vol.% Ar atmosphere up to 100 h. The 3D C/SiC composites with the modified coating system had a good oxidation resistance. This resulted in the high strength retained ratio of the composites even after the oxidation.     

A modified dual-layer SiC oxidation protective coating for carbon/carbon composites prepared by one-step pack cementation

To improve the oxidation resistance of SiC coating produced by pack cementation for carbon/carbon composites, a modified SiC coating has been produced by one-step pack cementation by adding ferrocene in pack compositions. The as-received coating exhibited a dual-layer dense structure, and oxidation protective ability of SiC coating could be improved by introducing ferrocene. The modified coating could protect C/C composites from oxidation for more than 100 h at 1673 K in air. The weight loss of the coated C/C composites was considered to arise from deflection of penetrating cracks formed in outer layer from inner layer to C/C matrix.     

Effect of ozone adsorption on the oxidation behaviour of ZrB2–SiC ceramic composites

Ceramics of ZrB₂–20 vol.% SiC were prepared by hot pressing method, and ozone (O₃) was adsorbed on the surface of the ceramics. Then the as-adsorbed ceramics were oxidized in air and the effect of ozone adsorption on the oxidation behaviour of the ceramic composites was analyzed. The experimental results indicate that adsorption of ozone promotes the oxidation of the ceramic composites, especially for the SiC. In addition, more silica glass formed promotes the formation and crystal growth of zircon.     

Influence of SiC nanowires on the properties of SiC coating for C/C composites between room temperature and 1500 °C

To prevent carbon/carbon (C/C) composites from oxidation between room temperature and 1500 °C, a dense SiC nanowire-toughened SiC oxidation resistant coating was prepared by a two-step technique composed of chemical vapor deposition and pack cementation. SiC nanowires could effectively baffle the propagation of the microcracks and avoid the formation of the through-thickness microcracks in the original coating. The results indicated that, after introducing SiC nanowires, the coefficient of thermal expansion of the coating was decreased between 100 and 1500 °C, and the oxidation protective ability for the coated C/C composites was improved largely between room temperature and 1500 °C.     

B2O3 modified SiC–MoSi2 oxidation resistant coating for carbon/carbon composites by a two-step pack cementation

To protect carbon/carbon (C/C) composites against oxidation, a B₂O₃ modified SiC–MoSi₂ coating was prepared by a two-step pack cementation. The microstructure and the oxidation resistant property of the coating were studied. The results show that, the as-received coating is a dense structure, and is composed of α-SiC, β-SiC and MoSi₂. The B₂O₃ modified SiC–MoSi₂ coating has excellent oxidation resistant property, and can protect C/C composites from oxidation at 1773 K in air for more than 242 h. The failure of the coating was considered to arise from the existence of the penetration cracks in the coating during the slow cooling from 1873 to 673 K.     

Influence of preparation temperature on the oxidation resistance and mechanical properties of C/SiC coated C/C composites

A C/SiC oxidation resistance coating was prepared on carbon/carbon (C/C) composites by slurry and pack cementation. The microstructure, oxidation resistance and mechanical properties of C/SiC coating prepared from 1773 to 2573 K were investigated. With the increase of the preparation temperature, the oxidation resistance of C/SiC coating increases, however, the flexure strength decreases gradually. The preparation of C/SiC coating on C/C composites results in the fracture behavior of C/C composites changing from pseudo-plastic to brittle failure model. The decrease of flexure strength is mainly attributed to the decrease of C/C matrix’ flexure strength at high temperature.     

Oxidation protection of C/SiC coated carbon/carbon composites with Si–Mo coating at high temperature

To protect carbon/carbon (C/C) composites against oxidation, a Si–Mo coating was prepared on C/SiC-coated C/C composites by a simple slurry method. The microstructure of the coating was characterized by X-ray diffraction, scanning electron microscopy and Raman spectra. Results showed that the coating was mainly composed of SiC, MoSi₂ and Si. It could protect C/C composites from oxidation at 1873 K in air for 300 h and withstand 13 thermal cycles between room temperature and 1873 K. The excellent oxidation and thermal shock resistance of the coating was attributed to the formation of dense SiO₂ glass at high temperature. The volatilization of MoO₃ and SiO₂ at 1873 K was the main reason of the weight loss of the coated C/C composites.     

Dynamic oxidation of ultra-high temperature ZrB2–SiC under high enthalpy supersonic flows

The dynamic response to oxidation of a hot-pressed ZrB₂ + 15 vol%. SiC ceramic composite was studied under aero-thermal heating using a high enthalpy supersonic flow of a N₂/O₂ gas mixture in plasma wind tunnel. Microstructural features of the reaction scale developed upon oxidation were analyzed and correlated to test conditions through Computational Fluid Dynamics simulations. The significant heat flux and temperature gradients of the sample’s surface exposed to the highly energized N₂/O₂ gas stream led to the formation and evolution of distinct layered oxide sub-scales. The diffusion of oxidants through silica-rich 3D glassy network was proposed as the rate governing factor for oxidation.     

Comparison of thermal and ablation behaviors of C/SiC composites and C/ZrB2-SiC composites

A comparison was presented of the thermal and ablation behaviors of two carbon fiber reinforced ceramic-matrix composites (one with a SiC matrix and the other with a ZrB₂-SiC matrix). The C/SiC composite possessed a lower thermal conductivity (TC) and a higher emissivity in comparison to the C/ZrB₂-SiC composite. The two composites exhibited the good ablation-resistive properties with no obvious erosion rate after the arc-heated wind tunnel ablation tests. The surface of the C/SiC composite appeared to be coarse and had many rounded protrusions while a denser and more homogeneous glass oxide scale was formed for the C/ZrB₂-SiC composite. The maximum surface and back side temperatures of the C/ZrB₂-SiC composite were about 50 °C lower than those of the C/SiC composite, respectively, which was mainly attributed to the evaporation of the B₂O₃ as well as its higher TC.     

Ablation behavior of ZrB2–SiC–ZrO2 ceramic composites by means of the oxyacetylene torch

Ablation behavior of ZrB₂–SiC–ZrO₂ ceramics with two ZrO₂ contents was investigated using oxyacetylene torch. Thermogravimetric analysis demonstrated that ceramic with 10 vol% ZrO₂ showed initial weight change at higher temperature than the one with 20 vol% ZrO₂. After same ablation condition, lighter oxidized microstructure and lower weight loss and line gain were obtained from ceramic with 10 vol% ZrO₂. Ablation mechanism revealed that excessive ZrO₂ would supply much path to the inward transport of oxygen, which led to the dissatisfactory resistance to oxidation and ablation for the ceramic with 20 vol% ZrO₂.     

Oxidation behaviour of Al2O3–TiC–Co composites at 800–1000 °C in air

The oxidation behaviour of nanometre and micrometre sized Al₂O₃–TiC–Co composites is investigated at 800–1000 °C in air for 25 h. The oxidation resistance of nanometre sized samples is better than of micrometre sized. Phase compositions and microstructures were studied by XRD and SEM. The values of general rate constant k and oxidation exponent n are dependent on oxidation temperature and composites. The oxidation kinetics followed a rate that is slightly faster than the parabolic-rate law at 800–1000 °C. The activation energy of the nanometre sized is higher than of micrometre sized in the range of 800–1000 °C.     

Oxidation mechanism of a ZrB2–SiC–ZrC ceramic heated through high frequency induction at 1600 °C

In the present work, isothermal oxidation of a ZrB₂–(20 vol.%) SiC–(6 vol.%) ZrC (ZrB₂–SiC–ZrC) ceramic was carried out at a constant temperature of 1600 ± 15 °C in static air, and the microstructures of the surface and fractured surface of the oxidised specimen were observed using SEM. The change curve of weight change/unit area with increasing oxidation time was composed of four stages according to the increase in the oxidation time: initial, middle, middle-late and late. In the different stages, a mathematical model was formulated to interpret the oxidation behaviour of the ZrB₂–SiC–ZrC ceramic at high temperature.     

Oxidation mechanism and resistance of ZrB2–SiC composites

The oxidation mechanism of ZrB₂–SiC composites was investigated based on a combination of theory and experiments. The oxidation reactions, microstructure evolution, scale stability and temperature limit were examined in our research and a good correspondence was obtained between theoretical predictions and experimental results. Microstructure evolution and stability are significantly dependent on both temperature and composition. SiO₂ is thermochemically stable below 1800 °C and will lose its protective properties at temperatures above 2300 °C. The temperature limit for ZrB₂–SiC composites is strongly dependent on the vapor pressure of the gaseous products and volume content of ZrB₂.     

The effect of zirconium carbide on ablation of carbon/carbon composites under an oxyacetylene flame

Ablation of zirconium carbide (ZrC) modified carbon/carbon (C/C) composites was tested by an oxyacetylene torch. The formation of zirconia from the oxidation of ZrC improves the ablation resistance of the C/C composites because of the evaporation at elevated temperature, which absorbs heat from the flame and reduces the erosive attack to carbon. Zirconia also acts as an accelerator for carbon oxidation as it reacts with carbon during the ablation, increasing the mechanical breakage rate of the fibres. However, the effect of mechanical breakage is inferior in the ablation of the composites. The heterogeneous reactions control the ablation of the composites.     

A MoSi2-SiC-Si oxidation protective coating for carbon/carbon composites

To protect carbon/carbon (C/C) composites from oxidation, a dense coating has been produced by a two-step pack cementation technique. XRD and SEM analysis shows that the as-obtained coating was composed of MoSi₂, SiC and Si with a thickness of 80-100 μm. The MoSi₂-SiC-Si coating has excellent anti-oxidation property, which can protect C/C composites from oxidation at 1773 K in air for 200 h and the corresponding weight loss is only 1.04%. The weight loss of the coated C/C composites is primarily due to the reaction of C/C substrate and oxygen diffusing through the penetration cracks in the coating.     

Microstructural evolution of coating-modified 3D C/SiC composites after annealing in wet oxygen at different temperatures

Two types of coating-modified 3D C/SiC, coated with CVD SiC/SiC/SiC (type I) and CVD SiC/amorphous-BC/SiC (type II), are subjected to a 14 vol.% H₂O/8 vol.% O₂/78 vol.% Ar atmosphere at 700, 1000 and 1200 °C up to 100 h. Microstructure and corrosion behaviour are investigated using a variety of characterization techniques. The type II shows a better oxidation resistance than type I during annealing at relatively low temperatures. Nevertheless, residual strength of the type I annealed above 1000 °C is enhanced by healing of many micron-sized defects. Interfacial bond strength of the composites is reasonably improved after annealing.