Modeling of the effect of Al2O3 interlayer on residual stress due to oxide scale in thermal barrier coatings

Limarga, Andi M.; Widjaja, Sujanto; Yip, T.H.; Teh, L.K.

doi:10.1016/s0257-8972(01)01545-6

Cited by 49 publications

(12 citation statements)

References 14 publications

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“…For high-temperature applications, such as aeronautics, incinerators or industrial turbines, alumina-forming alloys have proved to be very good candidates for oxidation and corrosion resistance. [1][2][3][4][5][6][7][8][9][10][11][12] The best protection is based on the formation of an Al 2 O 3 layer which exhibits good mechanical resistance, high thermal and chemical stability, interesting dielectric and optical properties.…”

Section: Introductionmentioning

confidence: 99%

High-Temperature-Oxidation Behavior of Iron–Aluminide Diffusion Coatings

2006

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Aluminide diffusion coatings were oxidized in air under atmospheric pressure under isothermal and cyclic conditions. The high-temperature efficiency of the pack-aluminized alloys was tested by comparing their oxidation behavior in the temperature range 800-1080°C. The k p values deduced from the parabolic plots of weight-gain curves showed that a-Al 2 O 3 composed the major phase of the oxide scale on samples oxidized at T > 1000°C. For lower temperatures, transient-alumina phases were observed. The aluminide materials also exhibited excellent resistance to cyclic oxidation at 1000°C. The second aim of this study was to dope the aluminide compounds obtained by a pack-cementation process with yttria, which was introduced by metal-organic chemical-vapor deposition (MOCVD). The beneficial effect of the reactive-element-oxide coating is strongly dependent on its mode of introduction, since the oxidation resistance is drastically increased when the Y 2 O 3 coating was applied prior to the aluminization process. When applied after the aluminization, the reactive element gave negative effects on the high-temperature oxidation behavior of the iron aluminides. The oxide morphologies, X-ray diffraction patterns and two-stage experiments helped to understand the oxide-scale-growth mechanisms.

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Section: Introductionmentioning

confidence: 99%

High-Temperature-Oxidation Behavior of Iron–Aluminide Diffusion Coatings

2006

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“…These tensile stresses, acting on the pre-existing flaws and defects, would promote crack initiation and delamination in the coating system [2,[15][16][17][18]. Finite-element analyses have shown that the stresses in a TBC increase with a growing TGO layer [19][20][21].…”

Section: Introductionmentioning

confidence: 99%

Oxidation and crack nucleation/growth in an air-plasma-sprayed thermal barrier coating with NiCrAlY bond coat

Chen

Marple

et al. 2005

Surface and Coatings Technology

164

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The oxidation behavior of an air-plasma-sprayed thermal barrier coating (APS-TBC) system was investigated in both air and low-pressure oxygen environments. It was found that mixed oxides, in the form of (Cr,Al) 2 O 3 d Ni(Cr,Al) 2 O 4 d NiO, formed heterogeneously at a very early stage during oxidation in air, and in the meantime, a layer of predominantly Al 2 O 3 grew rather uniformly along the rest of the ceramic/bond coat interface. The mixed oxides were practically absent in the TBC system when exposed in the low-pressure oxygen environment, where the TBC had a longer life. Through comparison of the microstructures of the APS-TBC exposed in air and low-pressure oxygen environment, it was concluded that the mixed oxides played a detrimental role in causing crack nucleation and growth, reducing the life of the TBC in air. The crack nucleation and growth mechanism in the air-plasma-sprayed TBC is further elucidated with emphasis on the Ni(Cr,Al) 2 O 4 and NiO particles embedded in the chromia. D

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“…Prominent among these factors are the TGO growth, rumpling in the bond coat, microstructural changes in the bond coat and ceramic coating. Even sintering of the columns in the ceramic layer over long periods of high temperature exposure (Sujanto Widjaja et al, 2003;Limarga et al, 2002;He et al, 2000) and creep deformation (Hutchinson, 2001) can also lead to changes in stresses in the TBC. The effect of rumpling has been already discussed in our earlier paper (Srivathsa et al, 2011) and the effect of dynamic growth of TGO is currently under study.…”

Section: Stress Variation Over 1000 Thermal Cyclesmentioning

confidence: 99%

Parametric Studies Of Failure Mechanisms In Thermal Barrier Coatings During Thermal Cycling Using FEM

Srivathsa¹,

Das²

2015

International Journal of Applied Mechanics and Engineering

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Thermal barrier coatings (TBCs) are widely used on different hot components of gas turbine engines such as blades and vanes. Although, several mechanisms for the failure of the TBCs have been suggested, it is largely accepted that the durability of these coatings is primarily determined by the residual stresses that are developed during the thermal cycling. In the present study, the residual stress build-up in an electron beam physical vapour deposition (EB-PVD) based TBCs on a coupon during thermal cycling has been studied by varying three parameters such as the cooling rate, TBC thickness and substrate thickness. A two-dimensional thermomechanical generalized plane strain finite element simulations have been performed for thousand cycles. It was observed that these variations change the stress profile significantly and the stress severity factor increases nonlinearly. Overall, the predictions of the model agree with reported experimental results and help in predicting the failure mechanisms.

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Modeling of the effect of Al2O3 interlayer on residual stress due to oxide scale in thermal barrier coatings

Cited by 49 publications

References 14 publications

High-Temperature-Oxidation Behavior of Iron–Aluminide Diffusion Coatings

High-Temperature-Oxidation Behavior of Iron–Aluminide Diffusion Coatings

Oxidation and crack nucleation/growth in an air-plasma-sprayed thermal barrier coating with NiCrAlY bond coat

Parametric Studies Of Failure Mechanisms In Thermal Barrier Coatings During Thermal Cycling Using FEM

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