Thermal Barrier Coatings on Copper Substrates for Rocket Applications

Schloesser, J.; Федорова, Т. Г.; Bäker, Martin; Rösler, Joachim

doi:10.1299/jmmp.4.189

Cited by 9 publications

(3 citation statements)

References 7 publications

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“…At the interface between the ceramic thermal barrier coating and the bond coat no thermally grown oxide formed in the studied specimens (compare also ref. [9]).…”

Section: Thermal Cycling Experimentsmentioning

confidence: 99%

Oxidation Behavior of Thermal Barrier Coatings on Copper Substrates

Schloesser

Bäker

Rösler

et al. 2010

Advances in Science and Technology

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In rocket engine combustion chambers, the cooling channels experience extremely high temperatures and environmental attack. Thermal protection can be provided by Thermal Barrier Coatings. Due to the need of good heat conduction, the inner combustion liner is made of copper. The performance of a standard coating system for nickel based substrates is investigated on copper substrates. Thermal cycling experiments are performed on the coated samples. Due to temperature limitations of the copper substrate material, no thermally grown oxide forms at the interface of the thermal barrier coating and the bond coat. Delamination of the coatings occurs at the interface between the substrate and the bond coat due to oxide formation of the copper at uncoated edges. In real service a totally dense coating can probably not be assured which is the reason why this failure mode is of importance. Different parameters are used for thermal cycling to understand the underlying mechanisms of delamination. Furthermore, laser heating experiments account for the high thermal gradient in real service. Pilot tests which led to a delamination of the coating at the substrate interface were performed successfully.

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“…At the interface between the ceramic thermal barrier coating and the bond coat no thermally grown oxide formed in the studied specimens (compare also ref. [9]).…”

Section: Thermal Cycling Experimentsmentioning

confidence: 99%

Oxidation Behavior of Thermal Barrier Coatings on Copper Substrates

Schloesser

Bäker

Rösler

et al. 2010

Advances in Science and Technology

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“…In a first step, state of the art thermal barrier coatings, consisting of a NiCrAlY bond-coat and a zirconia top-coat, were tested to gain a better understanding of the coating failure mechanisms [12][13][14]. A laser test bed has been set up to test the coatings with a thermal gradient [13], and a micro model was developed to investigate interface stresses between substrate and coating which led to delaminations during the laser tests [12].…”

Section: Introductionmentioning

confidence: 99%

Mechanical Integrity of Thermal Barrier Coatings: Coating Development and Micromechanics

Fiedler

Rösler

Bäker

et al. 2020

Notes on Numerical Fluid Mechanics and Multidisciplinary Design

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To protect the copper liners of liquid-fuel rocket combustion chambers, a thermal barrier coating can be applied. Previously, a new metallic coating system was developed, consisting of a NiCuCrAl bond-coat and a Rene 80 top-coat, applied with high velocity oxyfuel spray (HVOF). The coatings are tested in laser cycling experiments to develop a detailed failure model, and critical loads for coating failure were defined. In this work, a coating system is designed for a generic engine to demonstrate the benefits of TBCs in rocket engines, and the mechanical loads and possible coating failure are analysed. Finally, the coatings are tested in a hypersonic wind tunnel with surface temperatures of 1350 K and above, where no coating failure was observed. Furthermore, cyclic experiments with a subscale combustion chamber were carried out. With a diffusion heat treatment, no large-scale coating delamination was observed, but the coating cracked vertically due to large cooling-induced stresses. These cracks are inevitable in rocket engines due to the very large thermal-strain differences between hot coating and cooled substrate. It is supposed that the cracks can be tolerated in rocket-engine application.

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“…The use of thermal barrier coatings together with anchoring systems allows this equipment to be subjected to temperatures as high as the melting temperature of some of the metals in the superalloys, which are on the order of 1080 °C. The use of thermal barrier coatings reduces metal temperature and increases the lifespan of turbine components (Schloesser et al 2010;Gleeson 2006).…”

Section: Introductionmentioning

confidence: 99%

Effect of the Addition of La2O3 on the Properties of ZrO2-Al2O3 Ceramic Composites for Coatings in Aerospace Turbines

Gomes

Domingues

Silva

et al. 2020

J.Aerosp. Technol. Manag.

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Ceramic matrix composites have attracted the interest of turbine manufacturers for use in coating hot sections because of their higher capacity to withstand high temperatures and because they have a lower requirement for air cooling. One of the most commonly used ceramic coatings is zirconia-yttria. However, its main disadvantage is the inherent fragility of ceramics, which limits the use of these materials in mechanical structures and industrial applications. Ceramics are generally reinforced with the incorporation of additives to reduce their brittleness and increase their mechanical strength and toughness. It is known that La2O3 which are potential source for stabilization of zirconia composites. In this context, ZrO2-Al2O3-La2O3 based ceramic matrix composites were developed for deposition of a thermal barrier coating on the substrate of exhaust nozzles of aerospace turbines varying the content of La2O3 by 5, 7 and 10 wt%. The composites were produced by a thermomechanical process and sintered at 1385 °C. The properties of these composites were studied by X-ray diffraction, relative density, scanning electron microscopy, and Vickers microhardness tests. The results indicate that the composite with 10% La2O3 has great potential for use as ceramic coatings of turbine exhaust nozzles in the aerospace industry.

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Thermal Barrier Coatings on Copper Substrates for Rocket Applications

Cited by 9 publications

References 7 publications

Oxidation Behavior of Thermal Barrier Coatings on Copper Substrates

Oxidation Behavior of Thermal Barrier Coatings on Copper Substrates

Mechanical Integrity of Thermal Barrier Coatings: Coating Development and Micromechanics

Effect of the Addition of La2O3 on the Properties of ZrO2-Al2O3 Ceramic Composites for Coatings in Aerospace Turbines

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