Fabrication of W/Cu composite coatings by supersonic atmosphere plasma spraying and their anti-ablation performance under oxyacetylene torch

Guo, Lingjun; Peng, Jian; Wang, Hai-Qi; Kou, Gang; Huo, Caixia

doi:10.1016/j.jallcom.2017.01.281

Cited by 18 publications

(5 citation statements)

References 31 publications

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“…For passive thermal protection systems, currently available materials have shortcomings when it comes to high temperature and oxidation resistance [28]. In addition, passive thermal protection systems of combined propulsion also need to bear enough mechanical loads and have excellent performance in ablation resistance, which were rarely explored in past researches [29]. For current active thermal protection systems, as the Mach number increases, the temperature of the incoming flow increases, resulting in a decline in convective cooling of the air.…”

Section: Overviewmentioning

confidence: 99%

Thermal Protection System and Thermal Management for Combined-Cycle Engine: Review and Prospects

et al. 2019

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Combined-cycle engine is a potential propulsion system for hypersonic aircraft. To ensure long-term, normal operation of combined-cycle engine under the harsh environment of high thermal load, it is of great significance to study the thermal protection and management of the propulsion system. In this study, the objective and development status of thermal protection and thermal management systems for the combined-cycle propulsion system were described. The latest research progresses of thermal protection, thermal barrier coating, and thermal management system of the combined-cycle propulsion system were summarized. Moreover, the problems and shortcoming in current researches were summarized. In addition, a prospect for the future development of thermal protection and management of the combined-cycle propulsion system was presented, pointing out a direction of great value and vital research significance to thermal protection and management of the combined-cycle propulsion system.

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Section: Overviewmentioning

confidence: 99%

Thermal Protection System and Thermal Management for Combined-Cycle Engine: Review and Prospects

et al. 2019

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“…Additionally, W can serve as a bonding layer to improve the adhesion and stability of the coating to the substrate. Guo et al [ 24 ] prepared W/Cu coatings on C/C composites by a supersonic spraying process, with a 63% reduction in linear ablation rate when compared to pure W coatings after oxyacetylene flame ablation. The thermal expansion of the coating was reduced by the sweating and cooling effect of Cu, but the bond strength to the matrix was reduced.…”

Section: Introductionmentioning

confidence: 99%

Oxidative Ablation Behavior of W‐Coated C/C Composites Prepared by Chemical Vapor Deposition with Heat Treatment

et al. 2023

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“…The coating technique is considered to be an effective method to address this problem as it can directly cut off the diffusion channel for oxidizing gases. [ 8,9 ] Tungsten (W) is the most commonly used material for elevated‐temperature applications, such as plasma‐facing material (PFM) in some existing tokamaks (ASDEX‐Upgrade, JET) [ 10,11 ] and rocket engine components. [ 8,9,12,13 ] W boasts some interesting unique properties, including a high melting point, good corrosion resistance, and low vapor pressure.…”

Section: Introductionmentioning

confidence: 99%

“…[ 8,9 ] Tungsten (W) is the most commonly used material for elevated‐temperature applications, such as plasma‐facing material (PFM) in some existing tokamaks (ASDEX‐Upgrade, JET) [ 10,11 ] and rocket engine components. [ 8,9,12,13 ] W boasts some interesting unique properties, including a high melting point, good corrosion resistance, and low vapor pressure. [ 10–14 ] Previous studies [ 15 ] show that the W layer prepared by atmospheric plasma spray (APS) on the surface of C/C composites exhibit better ablation resistance compared with uncoated composites.…”

Section: Introductionmentioning

confidence: 99%

Microstructure and Ablation Behavior of W/ZrC/SiC Coating on C/C Composites Prepared by Reactive Melt Infiltration and Atmospheric Plasma Spraying

Zhou

Niu

et al. 2021

Adv Eng Mater

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A W/ZrC/SiC multilayer coating is prepared on carbon/carbon (C/C) composites by reactive melt infiltration (RMI) and atmospheric plasma spray (APS). The morphology and microstructure of the coating are characterized by scanning electron microscopy coupled with energy dispersive spectrometry (SEM‐EDS), X‐ray diffraction (XRD), and focused ion beam (FIB) and transmission electron microscopy (TEM). Microstructure analysis reveals that the gradient coatings exhibit smooth surface morphology, well‐defined interfaces, uniform thickness, and a highly dense architecture. After 60 s of ablation, the linear ablation rates (LARs) and mass ablation rates (MARs) of the coated composites stand at 2.58 × 10−3 mm s−1 and 5.25 × 10−3 g s−1, respectively. In general, the reason for the great ablation resistance of W/ZrC/SiC‐coated C/C composites is the comprehensive effect of the multilayer coating. The outer W coating is used as the first barrier layer to resist most thermal shocks. Then, the molten eutectics SiO2–ZrO2 formed in the ZrC/SiC layer at service temperature can fill the pores and act as a second diffusion barrier for oxygen and heat.

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Fabrication of W/Cu composite coatings by supersonic atmosphere plasma spraying and their anti-ablation performance under oxyacetylene torch

Cited by 18 publications

References 31 publications

Thermal Protection System and Thermal Management for Combined-Cycle Engine: Review and Prospects

Thermal Protection System and Thermal Management for Combined-Cycle Engine: Review and Prospects

Oxidative Ablation Behavior of W‐Coated C/C Composites Prepared by Chemical Vapor Deposition with Heat Treatment

Microstructure and Ablation Behavior of W/ZrC/SiC Coating on C/C Composites Prepared by Reactive Melt Infiltration and Atmospheric Plasma Spraying

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