Investigation of Crack Propagation Behavior of Atmospheric Plasma-Sprayed Thermal Barrier Coatings under Uniaxial Tension Using the Acoustic Emission Technique

Wang, L.; Liu, C. G.; Zhong, Xinghua; Zhao, Yuehong; Zhao, Hao; Yang, Jianli; Tao, Shiqian; Wang, Y.

doi:10.1007/s11666-014-0207-x

Cited by 23 publications

(8 citation statements)

References 30 publications

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“…The shear stress region expands into the coating with the movement of particles, but the shear stress decreases immediately after the particle rebound and the residual stress is less than half the peak value. When the stress penetrates the coating, the stress builds up at the coating interface but only some residual stress is retained, which is less than the bonding strength of the damaged coating [32]. It can be seen that the coating greatly reduces the accumulation of residual stress among interfaces and avoids the premature failure of TBCs.…”

Section: Protection Of Coating To Substratementioning

confidence: 99%

Effect of Morphology, Impact Velocity and Angle of the CaO-MgO-Al2O3-SiO2 (CMAS) Particle on the Erosion Behavior of Thermal Barrier Coatings (TBCs): A Finite Element Simulation Study

et al. 2022

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The erosion of the unmelted CaO-MgO-Al2O3-SiO2 (CMAS) particle is one of the dominating factors that causes microcracks in thermal barrier coatings (TBCs) when an aeroengine operates under actual service conditions. The microcracks provide a pathway for the erosion of the TBCs by the molten CMAS particles, which accelerates the failure of the coating. Herein a simplified model to mimic the erosion of YSZ (Y2O3 stabilized ZrO2) TBCs by the CMAS particles with high speed is proposed. The finite element method was utilized to systematically investigate the physical damage behaviors of the TBCs by the CMAS particles under various contact configurations, impact velocities and impact angles. We show that the contact configuration has a significant impact on the residual stress of the coating surfaces as well as the formation and types of microcracks. Furthermore, the increment of the erosion velocity gave rise to irreversible deformation around the point of contact, which aggravated the stress conditions of the top layer and led to the delamination failure of the coating. Finally, the larger the erosion angle, the more mechanical energy was converted into internal energy, which accumulated in the YSZ and caused it to finally delaminate.

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Section: Protection Of Coating To Substratementioning

confidence: 99%

Effect of Morphology, Impact Velocity and Angle of the CaO-MgO-Al2O3-SiO2 (CMAS) Particle on the Erosion Behavior of Thermal Barrier Coatings (TBCs): A Finite Element Simulation Study

et al. 2022

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“…The actual failure of APS-TBCs is due to the shedding of the metallic coating on the substrate, and the propagation of horizontal cracks along the interface of the substrate/bond-coat under bending moment. Sun et al [79] compared different samples using real three-dimensional morphologies via finite element modeling, and pointed out that this modeling method is an effective tool to obtain valuable research progress of stress distribution in TBCs. The results of finite element analysis indicated that the residual stress of TBCs is driven by the shear stress and the axial stress of La 2 Zr 2 O 7 (LZO).…”

Section: Roughness Of the Interfacementioning

confidence: 99%

Research Progress of Failure Mechanism of Thermal Barrier Coatings at High Temperature via Finite Element Method

Liu

Wang

et al. 2020

Coatings

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In the past decades, the durability of thermal barrier coatings (TBCs) has been extensively studied. The majority of researches emphasized the problem of oxidation, corrosion, and erosion induced by foreign object damage (FOD). TBCs with low thermal conductivity are usually coated on the hot-section components of the aircraft engine. The main composition of the TBCs is top-coat, which is usually regarded as a wear-resistant and heat-insulating layer, and it will significantly improve the working temperature of the hot-section components of the aircraft engine. The application of TBCs are serviced under a complex and rigid environment. The external parts of the TBCs are subjected to high-temperature and high-pressure loading, and the inner parts of the TBCs have a large thermal stress due to the different physical properties between the adjacent layers of the TBCs. To improve the heat efficiency of the hot-section components of aircraft engines, the working temperature of the TBCs should be improved further, which will result in the failure mechanism becoming more and more complicated for TBCs; thus, the current study is focusing on reviewing the failure mechanism of the TBCs when they are serviced under the actual high temperature conditions. Finite element simulation is an important method to study the failure mechanism of the TBCs, especially under some extremely rigid environments, which the experimental method cannot realize. In this paper, the research progress of the failure mechanism of TBCs at high temperature via finite element modeling is systematically reviewed.

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“…Normally, EB-PVD-TCs show a columnar grains structure and APS-TCs show a lamellar structure. The strain tolerance of columnar-structured coatings is higher due to a smaller increase in global elastic modulus during thermal shock resistance [19], which extends the lifespan of TBCs [20][21][22][23][24]. In APS-TC, the micro-pores and cracks are dispensed haphazardly and resulted in low thermal conductivity.…”

Section: Introductionmentioning

confidence: 99%

Tailoring Periodic Vertical Cracks in Thermal Barrier Coatings Enabling High Strain Tolerance

Mehboob

et al. 2021

Coatings

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Lifetime is a basic support for the thermal insulation function of thermal barrier coatings (TBCs). Therefore, extending the life span is essential to develop next-generation TBCs. For this objective, the columnar structure formed by vertical cracks appears to make sense. However, the underlying mechanism is still unclear. This work scrutinizes the influence of periodic vertical cracks on cracking behavior in order to tailor high strain tolerant TBCs. A finite element model was evolved to explore the crack behavior influenced by thermal mismatch strain between substrate and coating. The virtual crack closure technique (VCCT) was used to describe the propagation of crack under load. It is found clearly that the space between two vertical cracks (short for SVC) along the in-plane direction has a noteworthy influence on the strain tolerance of TBCs. Results indicate that the strain energy release rate (SERR) and stresses at the pre-crack tip increase continuously with the increase of the SVC, suggesting that the driving force for cracks is increasing. The crack is not propagated when the SVC is very small, whereas the crack grows continuously with the increase of the SVC. The growth of a crack can be prevented by reducing the SVC. A critical value for the SVC was found. When the SVC is less than the critical value, the SERR can be dramatically reduced. Thus, the SVC of periodic cracks can be tailored to obtain TBCs with high strain tolerance.

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Investigation of Crack Propagation Behavior of Atmospheric Plasma-Sprayed Thermal Barrier Coatings under Uniaxial Tension Using the Acoustic Emission Technique

Cited by 23 publications

References 30 publications

Effect of Morphology, Impact Velocity and Angle of the CaO-MgO-Al2O3-SiO2 (CMAS) Particle on the Erosion Behavior of Thermal Barrier Coatings (TBCs): A Finite Element Simulation Study

Effect of Morphology, Impact Velocity and Angle of the CaO-MgO-Al2O3-SiO2 (CMAS) Particle on the Erosion Behavior of Thermal Barrier Coatings (TBCs): A Finite Element Simulation Study

Research Progress of Failure Mechanism of Thermal Barrier Coatings at High Temperature via Finite Element Method

Tailoring Periodic Vertical Cracks in Thermal Barrier Coatings Enabling High Strain Tolerance

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