Novel thermal barrier coatings repel and resist molten silicate deposits

Zhang, Baopeng; Song, Wenjia; Wei, Liangliang; Xiu, Yuxuan; Xu, Huibi; Dingwell, Donald B.; Guo, Hongbo

doi:10.1016/j.scriptamat.2018.12.028

Cited by 73 publications

(19 citation statements)

References 39 publications

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“…Aside from designing coatings to resist CMAS from an infiltration or reactive exfoliation perspective, there is also ongoing research to develop TBCs which intrinsically do not allow the CMAS melt to stay on the surface long enough for infiltration or even reaction to occur. Such "sand-phobic" TBCs have been proposed by research from Ghoshal et al [39,40,41], Zhang et al [42], and others [43]. However, even if materials become available that demonstrate such effects, interaction with these compliant TBC structures which are already in service is still an issue to consider.…”

Section: Introductionmentioning

confidence: 99%

Dynamic interactions of ingested molten silicate particles with air plasma sprayed thermal barrier coatings

Gildersleeve

Sampath

2020

J. Mater. Res.

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Section: Introductionmentioning

confidence: 99%

Dynamic interactions of ingested molten silicate particles with air plasma sprayed thermal barrier coatings

Gildersleeve

Sampath

2020

J. Mater. Res.

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“…For this reason, diverse physical methods were developed to deposit the ceramic top coat as a thermal barrier coating to the metallic substrate. The following methods are electron beam physical vapor deposition (EB-PVD), laser chemical vapor deposition, and atmospheric plasma sprayed, high-velocity oxy-fuel, sol-gel, plasma spray physical vapor deposition [1,34,35]. One of the most used of these kinds of application is electron beam physical vapor deposition (EB-PVD) and the second is atmospheric plasma spray (APS) [27,31,36].…”

Section: Thermal Barrier Coatingmentioning

confidence: 99%

Ceramic Composite Materials Obtained by Electron-Beam Physical Vapor Deposition Used as Thermal Barriers in the Aerospace Industry

et al. 2020

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This paper is focused on the basic properties of ceramic composite materials used as thermal barrier coatings in the aerospace industry like SiC, ZrC, ZrB 2 etc., and summarizes some principal properties for thermal barrier coatings. Although the aerospace industry is mainly based on metallic materials, a more attractive approach is represented by ceramic materials that are often more resistant to corrosion, oxidation and wear having at the same time suitable thermal properties. It is known that the space environment presents extreme conditions that challenge aerospace scientists, but simultaneously, presents opportunities to produce materials that behave almost ideally in this environment. Used even today, metal-matrix composites (MMCs) have been developed since the beginning of the space era due to their high specific stiffness and low thermal expansion coefficient. These types of composites possess properties such as high-temperature resistance and high strength, and those potential benefits led to the use of MMCs for supreme space system requirements in the late 1980s. Electron beam physical vapor deposition (EB-PVD) is the technology that helps to obtain the composite materials that ultimately have optimal properties for the space environment, and ceramics that broadly meet the requirements for the space industry can be silicon carbide that has been developed as a standard material very quickly, possessing many advantages. One of the most promising ceramics for ultrahigh temperature applications could be zirconium carbide (ZrC) because of its remarkable properties and the competence to form unwilling oxide scales at high temperatures, but at the same time it is known that no material can have all the ideal properties. Another promising material in coating for components used for ultra-high temperature applications as thermal protection systems is zirconium diboride (ZrB 2 ), due to its high melting point, high thermal conductivities, and relatively low density. Some composite ceramic materials like carbon-carbon fiber reinforced SiC, SiC-SiC, ZrC-SiC, ZrB 2 -SiC, etc., possessing low thermal conductivities have been used as thermal barrier coating (TBC) materials to increase turbine inlet temperatures since the 1960s. With increasing engine efficiency, they can reduce metal surface temperatures and prolong the lifetime of the hot sections of aero-engines and land-based turbines.

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“…With the increasing demand for high operating temperature of new gas-turbine engines, SiC-based ceramic matrix composite (SiC-CMC) materials have attracted great interest for their high-temperature tolerance, superior mechanical properties, low density [1][2][3][4]. Under the combustion environment of an engine, which contains heated steam or corrosives (such as sand and volcanic ash, generally known as CMAS), SiC-CMC materials suffer from severe degradation, especially for the accelerated oxidation induced by steam [5][6][7][8][9][10][11]. To prevent the deleterious environmental attack of SiC components, environmental barrier coatings (EBCs) were developed to cover the SiC surface.…”

Section: Introductionmentioning

confidence: 99%

Pressure Infiltration of Molten Aluminum for Densification of Environmental Barrier Coatings

Dong

Liu

Zhang

et al. 2021

Preprint

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Environmental barrier coatings (EBCs) effectively protect ceramic matrix composites (CMCs) from harsh engine environment, especially steam and molten salts. However, open pores inevitably formed during deposition process provide transport channels for oxidants and corrosives and lead to premature failure of EBCs. This work proposed a pressure infiltration densification method that blocked these open pores in the coatings. Results showed that it was difficult for aluminum to infiltrate spontaneously, but with the increase of external gas pressure and internal vacuum simultaneously, the molten aluminum obviously moved forward, but finally stopped infiltrating at a depth of a specific geometry. Based on the wrinkled zigzag pore model, a mathematical relationship between the critical pressure and the infiltration depth and the pore intrinsic geometry was established. Infiltration results confirmed this relationship, indicating that for a given coating, a dense thick film can be obtained by adjusting the internal and external gas pressures to drive the melt infiltration.

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Novel thermal barrier coatings repel and resist molten silicate deposits

Cited by 73 publications

References 39 publications

Dynamic interactions of ingested molten silicate particles with air plasma sprayed thermal barrier coatings

Dynamic interactions of ingested molten silicate particles with air plasma sprayed thermal barrier coatings

Ceramic Composite Materials Obtained by Electron-Beam Physical Vapor Deposition Used as Thermal Barriers in the Aerospace Industry

Pressure Infiltration of Molten Aluminum for Densification of Environmental Barrier Coatings

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