Ablation behavior of C/SiC composites in plasma wind tunnel

Luo, Lei; Wang, Yiguang; Liu, Liping; Duan, Liuyang; Wang, Guolin; Lu, Yongxin

doi:10.1016/j.carbon.2016.02.085

Cited by 106 publications

(24 citation statements)

References 44 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…The surface temperature of C/SiC-HfC composites reached a stable stage, then gradually increased, and finally reached another stable stage. This phenomenon was not found during ablation under the same conditions for C/SiC composite prepared by CVI process and C/SiC-HfC composite prepared by RMI process [20,31,37]. Considering that there was no significant change in energy output (mainly including radiation and conduction) from the sample after the temperature reached the first stable stage, the energy arriving at the sample likely increased, and eventually caused the surface temperature of the sample to rise.…”

Section: Resultsmentioning

confidence: 81%

“…When the heat flux was further increased to 5.1 MW/m 2 , a jump in surface temperature occurred during the ablation process. The temperature jump was also found during the ablation of C/SiC-HfC prepared by RMI and C/SiC under high heat flux condition [20,31,37]. When the sample HF4 was moved into the plasma flow, the surface temperature rapidly climbed to 1735 ℃.…”

Section: Resultsmentioning

confidence: 81%

“…Then, oxygen diffused from the surface of sample to the substrate through the oxide layer, while silicon oxide diffused from the oxide layer to the surface [20,36]. SiO 2 on the surface would be lost under the combined effects of atomic oxygen, high-temperature, and highspeed flow [37]. Besides, the active oxidation of SiC likely occurred under the HfO 2 -SiO 2 layer due to lower oxygen partial pressure here, which may be one of the reasons for the formation of voids under the oxide layer.…”

Section: Resultsmentioning

confidence: 99%

See 2 more Smart Citations

Ablation of C/SiC-HfC composite prepared by precursor infiltration and pyrolysis in plasma wind tunnel

Duan

Luo²,

Liu

et al. 2020

J Adv Ceram

Self Cite

View full text Add to dashboard Cite

Carbon fiber reinforced silicon carbide-hafnium carbide (C/SiC-HfC) composite was prepared by precursor infiltration and pyrolysis process. Then, ablation behavior of C/SiC-HfC was evaluated in plasma wind tunnel. It was found that oxide layer formed during ablation significantly influenced the surface temperature. Formation of dense HfO 2-SiO 2 layer under low heat flux led to stable surface temperature. Silica (SiO 2) on the surface was gradually consumed when heat flux increased, resulting in conversion of HfO 2-SiO 2 on the surface to HfO 2. Converted HfO 2 with high catalytic coefficient absorbed more energy, causing gradual increase in the surface temperature. Formed oxide layer was destroyed at high heat flux and high stagnation point pressure. After carbon fiber lost the protection of HfO 2-SiO 2 layer, it burned immediately, leading to surface temperature jump.

show abstract

Section: Resultsmentioning

confidence: 81%

Section: Resultsmentioning

confidence: 81%

Section: Resultsmentioning

confidence: 99%

See 1 more Smart Citation

Ablation of C/SiC-HfC composite prepared by precursor infiltration and pyrolysis in plasma wind tunnel

Duan

Luo²,

Liu

et al. 2020

J Adv Ceram

Self Cite

View full text Add to dashboard Cite

show abstract

“…Ultra-high-temperature materials have been widely used as key components in high-end equipment [1]. For example, the materials for thermal protection purposes of hypersonic vehicles can serve above 1800°C even to 2400°C temporarily [2]. The hot structures of the high thrust-weight ratio aero-engines can work long term above 1600°C [3].…”

Section: Introductionmentioning

confidence: 99%

“…However, due to the inherent brittleness, the thermal shock resistance of ceramics is poor [5,6]. To overcome this main drawback, ceramic matrix composites have been developed and are referred to as the most promising materials for ultra-high-temperature structural applications in thermal shock environments, such as the space vehicle's thermal protection systems and the exit cones of non-cooled liquid rocket engines [1,2]. Besides, coatings are often used to improve the resistance to temperature or protect the hot components in harsh environments and extend the component lifetimes [1,2].…”

Section: Introductionmentioning

confidence: 99%

Fracture Strength Behaviors of Ultra-High-Temperature Materials

Cheng

et al. 2019

Journal of Applied Mechanics

View full text Add to dashboard Cite

Ultra-high-temperature materials have been widely used as key components in high-end equipment. However, the existing studies are mainly conducted at room and moderate temperatures. Besides, they are mainly carried out by experiments. Theories on the temperature dependence of fracture strength are rarely reported. In this work, experimental methods for the ultra-high-temperature tensile properties of advanced materials and the elastic–plastic properties of coatings are developed, respectively, based on induction heating and radiation furnace heating technologies. A temperature-dependent fracture strength model for ceramics is proposed in the view of energy. The experimental methods and theoretical model are verified on the 2D plain-weave carbon fiber reinforced silicon carbide thermal structure composite, yttria-stabilized zirconia thermal barrier coating, and Si3N4 ceramics. The study shows that the mechanical properties of materials decrease significantly at ultra-high temperatures. The results are useful for the applications of ultra-high-temperature materials in thermal structure engineering.

show abstract

Lightweight C/SiC Ceramic Matrix Composite Structures with High Loading Capacity

Yin²,

et al. 2019

Adv Eng Mater

View full text Add to dashboard Cite

Lightweight is one of the key issues for ceramic matrix composites during application. A lightweight concept of lattice core sandwich panel structure is applied for C/SiC composite. In this paper, C/SiC composite lattice core sandwich panel structures with different core angles are proposed and manufactured by using precursor infiltration and pyrolysis (PIP) method. The density, microstructure, and lightweight efficiency, as well as bending behavior, out‐of‐plane compression behavior and in‐plane compression behavior of the lightweight C/SiC structures with different core angles are studied. It is found that the lightweight C/SiC composite lattice core sandwich panel structures can maintain an excellent combination of lightweight characteristic and high loading capacity. And it is believed that this work can give some understanding of C/SiC composite and their structures.

show abstract

Ablation behavior of C/SiC composites in plasma wind tunnel

Cited by 106 publications

References 44 publications

Ablation of C/SiC-HfC composite prepared by precursor infiltration and pyrolysis in plasma wind tunnel

Ablation of C/SiC-HfC composite prepared by precursor infiltration and pyrolysis in plasma wind tunnel

Fracture Strength Behaviors of Ultra-High-Temperature Materials

Lightweight C/SiC Ceramic Matrix Composite Structures with High Loading Capacity

Contact Info

Product

Resources

About