High heat dissipation design improves thermal protection on ultrahigh temperature ablation

ZrC has drawn wide attention as an anti-ablation coating material for lightweight C/C composites but is limited by the produced porous and loose ZrO₂ film. To address this issue, the second phase is introduced to improve the densification of the formed Zr-X-O film. Such as ZrC-SiC/TaC coating, the produced low-melting-point oxides, SiO₂ (T_m=1650 °C), Ta₂O₅ (T_m=1800 °C) and Zr₆Ta₂O₁₇ (T_m=1900 °C), helped to form a dense oxides film. However, the high service temperature causes heat accumulation and a large thermal stress gradient on the surface of the coatings, which will result in large local defects and accelerate the failure of the coating. To decrease the ablation heat accumulation, incorporating nanomaterials with high thermal conductivity is an effective strategy but is limited in practical applications due to the agglomeration. A core–shell structure is advantageous because it can endow the outer carbon shell with good dispersion and a thermal conduction network. However, achieving a uniformly dispersed core–shell structure within a dense coating remains challenging due to structural retention difficulty that is limited by complex preparation processes.

Recently, a team from Northwestern Polytechnical University, China, constructed polymer-derived SiC/TaC with a graphene shell, and prepared corresponding dense ZrC-SiC/TaC@C coating. This work not only explains the heat dissipation effect of carbon shell in ZrC–SiC/TaC coating on improving protective ability against ultrahigh temperature ablation, but also provides a constructive idea that the ablation resistance improvement can be improved by incorporating carbon nanomaterials.

The team published their work in Journal of Advanced Ceramics on July 30, 2024.

“In this report, we designed and constructed a thermally conductive nanonetwork with a ceramic@carbon core–shell structure. Polymer-derived SiC/TaC with a graphene carbon shell was synthesized and introduced into a ZrC coating by supersonic atmospheric plasma spraying. Incorporating carbon nanomaterials with high thermal conductivity could reduce the surface temperature of ablation coatings and then decrease the ablation heat accumulation. The surface temperatures of the ZrC–SiC/TaC@C and ZrC–SiC/TaC coatings reach 2032 and 2224 °C, respectively, corresponding to a temperature difference of nearly 200 °C. Compared with that of the ZrC–SiC/TaC coating, the R_l of the ZrC–SiC/TaC@C coating is lower, at only 0.009 μm/s, a decrease of 93.7%.” said Jia Sun, from School of Materials at Northwestern Polytechnical University (China), a senior expert whose research interests focus on the field of high-temperature ceramics material.

Other contributors include Yuyu Zhang, Xuemeng Zhang, Hongkang Ou, Qiangang Fu from the School of Materials at Northwestern Polytechnical University in Xi’an, China; Bozhe Wang from the System Design Institute of Hubei Aerospace Technology Academy in Wuhan, China.

This work was supported by the National Key R&D Program of China (Nos. 2022YFB3708600 and 2021YFA0715802), the National Natural Science Foundation of China (No. 52101098), the Aeronautical Science Foundation of China (No. 2022Z055053004), the Fund of Key Laboratory of National Defense Science and Technology (No. WDZC20235250505), the National Science and Technology Major Project (No. J2022-VI-0011-0042), the National Basic Scientific Research (No. JCKY2021607B035), and the Innovation Foundation for Doctor Dissertation of Northwestern Polytechnical University (No. CX2024006).

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