Thermal barrier coatings for gas turbine use

Wortman, David; Nagaraj, B. A.; Duderstadt, E. C.

doi:10.1016/0921-5093(89)90798-3

Cited by 130 publications

(45 citation statements)

References 2 publications

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“…II, we discuss the calculational details of our work and in Sec. II D we present test calculations with our set of input parameters for bulk ZrO 2 and Ni. In Sec.…”

Section: Introductionmentioning

confidence: 99%

“…The protective coatings allow fuel combustion to be carried out at the highest possible operating temperature ͑maximizing fuel efficiency͒. 2 Unfortunately, current TBC's fail after a sequence of heating and cooling cycles. 3 Zirconia-based materials are often chosen for TBC's, due to their high melting points, low thermal conductivity, similar coefficient of thermal expansion to that of Ni superalloys used to construct the engine parts, and excellent resistance to corrosion and thermal shock.…”

Section: Introductionmentioning

confidence: 99%

“…The spallation problem is often reduced by placing a bond coat in between the TBC and the metal, but under real life operating conditions, the bond coat is oxidized as well. 10,11 Therefore, a lot of effort 2,3 has been put into refining and optimizing TBC/bond coat/metal structures to meet engineering requirements. The search for design principles has hitherto been rather phenomenological; this is a consequence of the structural and chemical complexity of the TBC/bond coat/metal structures, together with the lack of nondestructive experimental probes for in situ atomic scale characterization of buried interfaces, let alone oxide surfaces.…”

Section: Introductionmentioning

confidence: 99%

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Adhesion of ultrathin ZrO2(111) films on Ni(111) from first principles

Christensen¹,

Carter

2001

The Journal of Chemical Physics

120

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We have studied the ZrO 2 ͑111͒/Ni͑111͒ interface using the ultrasoft pseudopotential formalism within density functional theory. We find that ZrO 2 (111) adheres relatively strongly at the monolayer level but thicker ceramic films interact weakly with the Ni-substrate. We argue that the cohesion changes character from dominantly image charge interactions for thick ceramic films to more covalent for monolayer ZrO 2 (111) films. We provide an analysis of energetic, structural and electronic aspects of the ZrO 2 /Ni interface as a function of the thickness of the oxide layer. We also address the role of the exchange-correlation density functional parameterization for modeling the oxide and metal/oxide interface and discuss the sensitivity of the supercell approximation for metal/oxide interface properties.

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“…II, we discuss the calculational details of our work and in Sec. II D we present test calculations with our set of input parameters for bulk ZrO 2 and Ni. In Sec.…”

Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

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Adhesion of ultrathin ZrO2(111) films on Ni(111) from first principles

Christensen¹,

Carter

2001

The Journal of Chemical Physics

120

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“…Existen dos tipos de barreras térmicas dependiendo del método de deposición: -ZEY depositada por proyección por plasma a presión atmosférica sobre un MCrAlY depositado también por proyección por plasma pero a presión reducida o por HVOF [31] y -ZEY depositada por ebPVD sobre un MCrAlY también depositado por proyección por plasma a presión reducida o por HVOF o sobre un aluminuro de platino depositado como ya se ha descrito en párrafos anteriores [32] (Fig. 20).…”

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High temperature corrosion resistant coatings for gas turbine components

Agüero

2007

Rev. metal.

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P Pa al la ab br ra as s c cl la av ve eOxidación. Corrosión. Recubrimientos. Generación eléctrica. Aeronáutica. Turbina.High temperature corrosion resistant coatings for gas turbine components A Ab bs st tr ra ac ct t Hot section gas turbine components are made of superalloys, developed to withstand high temperatures in conditions in which mechanical stresses are high and that require high surface stability. However, during the 50s it became evident that compositions resulting in high mechanical strength for these materials were not compatible with those offering optimal protection from the working environments. The idea of employing protective coatings over materials with high mechanical strength resulted therefore from this situation. Presently, both aeronautic and power generation turbines operate at temperatures within the 900-1400 °C, thanks to these coatings, indispensable for their correct operation. In this work, the principal degradation mechanisms in these operating conditions and the different type of coatings presently employed by the industrial sector are described, beginning by the oldest Ni or Co aluminides, following with the addition of other metals such as Pt, Cr, etc. to the former coatings in order to increase their useful life, continuing with the overlay MCrAlY coatings and finishing with the thermal barrier coating systems. Moreover, the corresponding deposition techniques industrially employed to deposit these coatings are described, and finally, an insight of the latest research lines currently being developed is also included.

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“…MCrAlY (M=Ni, Co) coatings are widely used as overlays or bond coats in thermal barrier coating (TBC) systems in aerospace engines and industrial gas turbines nowadays [1][2][3].…”

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confidence: 99%

A Continuous β-NiAl Layer Forming at the Interface of a MCrAlY and CMSX-4

Yuan

Peng

2015

J Therm Spray Tech

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Abstract.A large test sample of single crystal superalloy (CMSX-4) deposited with a MCrAlY coating of γ and β phases was subjected to a thermal-cycling fatigue (TCF) test at 1100 °C for about 300 cycles. Near the coating-substrate interface where an inner β-depletion zone often develops in the coating for other superalloy-MCrAlY systems, a continuous β-layer was formed instead for this particular system after the TCF test. The formation of the β-layer was related to the accumulation of Al at the interface. Simulations using an oxidation-diffusion model were carried out on this and a number of other superalloy-MCrAlY systems. It was derived that the formation of the β-layer at the interface was likely due to the high Al activity of CMSX-4 which resisted the inward diffusion of Al from the coating. The simulation results also indicated a positive effect provided by the formation of the β-layer on the coating's oxidation resistance.

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Thermal barrier coatings for gas turbine use

Cited by 130 publications

References 2 publications

Adhesion of ultrathin ZrO2(111) films on Ni(111) from first principles

Adhesion of ultrathin ZrO2(111) films on Ni(111) from first principles

High temperature corrosion resistant coatings for gas turbine components

A Continuous β-NiAl Layer Forming at the Interface of a MCrAlY and CMSX-4

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