Emittance and absorptance of the national aeronautics and space administration ceramic thermal barrier coating

Liebert, C. H.

doi:10.1016/0040-6090(78)90042-1

Cited by 25 publications

(12 citation statements)

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“…The pyrometer was fixed at a distance of 1 m from the substrate and was focused at the center of the substrate. The raw output from the pyrometer was iteratively corrected to take into account the emissivity of ZrO 2 (⑀ ‫ס‬ 0.7181 and 0.5681 at 300 and 800°C, respectively 15 ), which was assumed to be a linear function of the temperature.…”

Section: Temperature Measurementsmentioning

confidence: 99%

Mechanisms of ceramic coating deposition in solution-precursor plasma spray

et al. 2002

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The solution-precursor plasma spray (SPPS) method is a new process for depositing thick ceramic coatings, where solution feedstock (liquid) is injected into a plasma. This versatile method has several advantages over the conventional plasma spray method, and it can be used to deposit nanostructured, porous coatings of a wide variety of oxide and non-oxide ceramics for a myriad of possible applications. In an effort to understand the SPPS deposition process, key diagnostic and characterization experiments were performed on SPPS coatings in the Y2O3-stabilized ZrO2 (YSZ) system. The results from these experiments show that there are multiple pathways to SPPS coating formation. The atomized precursor droplets undergo rapid evaporation and breakup in the plasma. This is followed by precipitation, gelation, pyrolysis, and sintering. The different types of particles reach the substrate and are bonded to the substrate or the coating by sintering in the heat of the plasma. The precursor also reaches the substrate or the coating. This precursor pyrolyzes in situ on the substrate, either after it reaches a “cold” substrate or upon contact on a “hot” substrate and helps bond the particles. The coating microstructure evolves during SPPS deposition as the coating temperature reaches approximately 770 °C.

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Section: Temperature Measurementsmentioning

confidence: 99%

Mechanisms of ceramic coating deposition in solution-precursor plasma spray

et al. 2002

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“…In CFD analysis, fluid regions on thermal barrier coating has been defined as air and the following acceptance have been made. a) Steady-state conditions b) One-dimensional heat transfer by conduction through coating and metal substrate c) Emissitive value of the coating material is taken as 0.5 [Liebert 1978, Zhu et al 1999].…”

Section: Methodsmentioning

confidence: 99%

Modeling of Heat Transfer in Exhaust Nozzle of Gas Turbines

Altun

Böke

2009

Proceedings of International Symposium on Heat Transfer in Gas Turbine Systems

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Thermal barrier coatings (TBCs) are applied blades, vanes, combustion chamber walls and exhaust nozzles in gas turbines in order to protect the metallic parts and to increase performance at high temperatures. In this present work, numerical steady-state exhaust nozzle heat transfer mechanisms were studied. Radiation to the external surface of coating and conduction to the coating and superalloy nozzle were modeled. The effective heat transfer coefficient was simulated. This analysis includes the CFD model of gas, coating and metal parts.

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“…Non-oxide CMC's of C-SiC origin exhibit a high integral spectral emittance (e 0.85 at 1300 C [16,17] thus allowing the component to emit thermal energy by radiation ("radiation cooling") and effectively lowering the surface temperature. Catalycity of the surface during interaction with the shockwave plasma also contribute to the net surface temperature.…”

Section: Coating Strategies For Increasing the Emissivity Of All-oxidmentioning

confidence: 99%

Tailoring protective coatings for all‐oxide ceramic matrix composites in high temperature‐/high heat flux environments and corrosive media

Braue¹,

Mechnich

2007

Materialwissenschaft Werkst

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Dedicated to Prof. Wolfgang Bunk on the occasion of his 80 th birthdayThe application range of porous all-oxide ceramic matrix composites (CMCs) can be significantly extended through deposition of protective coating systems. Typical applications include protection against erosion, wear and foreign object damage as well as a reduced permeability. Environmental barrier coatings (EBC) are mandatory in order to guarantee sufficient lifetime of the CMC components under high temperature-, high heat flux conditions and corrosive attack (combustor liners, thermal protection systems for atmospheric reentry). Limited thermal stability of today's oxide fibers requires additional thermal barrier functionality for EBCs in order to keep the effective CMC bulk temperatures below 1200 C. Depending on the specific application DLR's coating concept for all-oxide CMCs is based on either a single reaction-bonded aluminium oxide (RBAO) coating or a hybrid coating system consisting of a RBAO bond coat followed by an EB-PVD YSZ/FSZ top coat and is highlighted for three case studies. Deposition techniques (magnetron sputtering, MOCVD) alternative to EB-PVD as well as the suitability of fibrous and cellular materials for thick EBC/TBC layers are explored.Keywords

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Emittance and absorptance of the national aeronautics and space administration ceramic thermal barrier coating

Cited by 25 publications

References 1 publication

Mechanisms of ceramic coating deposition in solution-precursor plasma spray

Mechanisms of ceramic coating deposition in solution-precursor plasma spray

Modeling of Heat Transfer in Exhaust Nozzle of Gas Turbines

Tailoring protective coatings for all‐oxide ceramic matrix composites in high temperature‐/high heat flux environments and corrosive media

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