Improving Contact Damage Resistance of Thermal Barrier Coatings by Incorporating Buffer Layer

2009 ◽  
Vol 620-622 ◽  
pp. 319-322
Author(s):  
Sung Il Jung ◽  
Young Seok Sim ◽  
Jae Hyun Kim ◽  
Je Hyun Lee ◽  
Yeon Gil Jung ◽  
...  

The effects of the introduction of a buffer layer between the bond and top coats on the indentation stress-strain behavior and the contact damage were investigated in air-plasma sprayed (APS) zirconia (ZrO2)–based thermal barrier coatings (TBCs). The microstructure is relatively continuous in the TBC system with the buffer layer, showing Zr, Ni, Cr, and Mg elements between the top and bond coats, whereas the Zr element suddenly disappears by passing the interface between the top and bond coats. The TBC system with the buffer layer shows less strain than that without the buffer layer in the higher stress regions above about 1.3 GPa, while both TBC systems become soft by forming the top coat in the lower stress regions compared with the substrate. The stress–strain curve in both TBC systems is dependent on the dwell time of thermal exposure condition. The TBC system with the buffer layer shows the lower stress-strain curves than that without the buffer layer in thermal cycles with the relatively short dwell time of 1 h, showing the reverse trend with the relatively long dwell time of 10 h. Subsurface damage in substrate is reduced at both indentation loads of P = 500 N and P = 2000 N by introducing the buffer layer, independent of thermal exposure. Therefore, the TBC system with the buffer layer is more efficient in protecting the substrate from contact environments than that without the buffer layer, showing cracking or delamination between the top coat and the buffer layer in the TBC system with the buffer layer.

2012 ◽  
Vol 260-261 ◽  
pp. 438-442
Author(s):  
Kang Hyeon Lee ◽  
Sang Won Myoung ◽  
Min Sik Kim ◽  
Seoung Soo Lee ◽  
Eun Hee Kim ◽  
...  

In this study, the relationship between microstructural evolution and mechanical properties of thermal barrier coatings (TBCs) has been investigated through different thermal fatigue systems, electric thermal fatigue (ETF) and flame thermal fatigue (FTF), including the thermal stability through the interface between the bond and top coats. The TBC system with the thicknesses of 300 µm in both the top and bond coats was prepared with METCO 204 NS and AMDRY 962, respectively, with the air plasma spray (APS) system using 9MB gun. To observe the oxidation resistance and thermal stability of TBC, the thermal exposure tests were performed with both thermal fatigue tests at a surface temperature of 850 °C with a temperature difference of 200 °C between the surface and bottom of sample, for 12,000 EOH in designed apparatuses. The hardness values are slightly increased due to the densification of top coat with increasing the thermal exposure time in both thermal fatigue tests. The influence of thermal fatigue condition on the microstructural evolution and interfacial stability of TBC is discussed.


Author(s):  
B. Jayaraj ◽  
B. Franke ◽  
S. Laxman ◽  
D. Miranda ◽  
J. Liu ◽  
...  

Thermal barrier coatings (TBCs) are widely used for thermal protection of hot section components in turbines for propulsion and power generation. Development of a robust non-destructive evaluation (NDE) technique for TBCs is essential for quality control, life assessment and health monitoring that will facilitate reliable application, efficient maintenance and prevention of catastrophic failure. In this study, degradation of TBCs was non-destructively evaluated by photostimulated luminsecence (PSLS) and microstructurally examined as a function of furnace thermal cycling carried out in air with 10-minute heat-up, 1-, and 10-hour dwell duration at 2050°F (1121°C), and 10-minute forced-air quench. TBCs examined in this study consisted of electron beam physical vapor deposited (EB-PVD) yttria-stabilized zirconia (YSZ) on grit-blasted (Ni,Pt)Al or as-coated (Ni,Pt)Al or shot-peened NiCoCrAlY bond coats and various superalloy substrates. Characteristics of subcritical-subsurface damage near the thermally grown oxide (TGO) were documented by cross-sectional scanning electron microscopy. Mechanisms of damage varied as a function of TBC type and thermal cycling dwell time, and included preferential grain boundary oxidation after ridge-induced micro-cracking, racheting and undulation of TGO/bond coat interface, internal oxidation of bond coats, and formation of Ni/Co-rich oxides. These microstructural observations are correlated to the evolution in compressive residual stress in the TGO scale determined by photostimulated luminescence shift, including stress-relief associated with subcritical cracking in the TGO scale, and stress-relaxation associated with racheting of the TGO/bond coat interface. Correlations between the microstructural development and the photostimulated luminescence from the TGO scale are discussed as a function of TBC type and thermal cycling dwell time.


2021 ◽  
Vol 320 ◽  
pp. 31-36
Author(s):  
Marek Góral ◽  
Tadeusz Kubaszek ◽  
Barbara Kościelniak ◽  
Marcin Drajewicz ◽  
Mateusz Gajewski

Thermal barrier coatings are widely used for protection of gas turbine parts against high temperature oxidation and hot corrosion. In present work the microstructural assessment of TBCs produced by atmospheric plasma spray (APS) method was conducted. Three types of ceramic powders were used: magnesia- stabilized zirconia oxide (Metco 210), yttria stabilized zirconia oxide (YSZ -Metco 204) and fine-grained YSZ – Metco 6700. As a base material the Inconel 713 was used as well and CoNiCrAlY was plasma sprayed (APS) as a bond coat. The thickness of all ceramic layers was in range 80 – 110 μm. The elemental mapping of cross-section of magnesia-stabilized zirconia showed the presence of Mg, Zr and O in outer layer. In the YSZ ceramic layer the Y, Zr and O were observed during elemental mapping. The isothermal oxidation test was conducted at 1100 °C for 500 h in static laboratory air. On all samples the delamination and spallation of ceramic layers was observed. Chemical composition analysis of coatings showed the presence of two areas: the first one contained elements from bond coats: Ni, Cr, Al, Co and second area contained O, Cr Co and O that suggest the scale formation. The obtained results showed the total degradation of all ceramic layers as a result of internal stresses in bond-coat. Microscopic analysis showed the areas with complete degradation of bond coats and formation of thick oxides layer.


2010 ◽  
Vol 67 (2) ◽  
pp. 95-101 ◽  
Author(s):  
Jae-Young Kwon ◽  
Sung-Il Jung ◽  
Sang-Yeop Lee ◽  
Pyung-Ho Lee ◽  
Je-Hyun Lee ◽  
...  

1999 ◽  
Vol 5 (S2) ◽  
pp. 854-855
Author(s):  
M.R. Brickey ◽  
J.L. Lee

Thermal barrier coatings (TBCs) insulate gas turbine hot section components from the hot (∽1200 - 1450°C) combustion gas exhaust stream. An airline company can save millions of dollars per year by using TBCs to protect vital engine components and to improve fuel efficiency. TBCs typically consist of an 8 wt.% yttria-partially-stabilized zirconia (YPSZ) ceramic topcoat deposited on a platinum-nickel-aluminide (Pt-Ni-Al) bondcoat covering a nickel-based superalloy substrate. Thermal exposure during YPSZ electron beam-physical vapor deposition (EB-PVD) and engine operation promotes the formation of a thermally grown oxide (TGO) between the Pt-Ni-Al and the YPSZ layers. Stresses can develop at the Pt-Ni-Al/TGO and TGO/YPSZ interfaces due to TGO growth and thermal expansion coefficient mismatch. These stresses eventually cause spallation of the YPSZ, leaving the metallic substrate vulnerable to high temperature degradation since exhaust temperatures are often higher than the melting temperature of most nickel-based superalloys (∽1200 - 1450°C).


Author(s):  
Z. Mutasim ◽  
C. Rimlinger ◽  
W. Brentnall

Laboratory testing was conducted on air plasma sprayed (APS) and electron beam-physical vapor deposited (EB-PVD) thermal barrier coatings (TBCs) applied onto nickel alloy specimens. As-coated chemistry, microstructure, and bond strength of the TBC systems were evaluated. Cyclic oxidation tests that simulated industrial gas turbine environments were also conducted on the various thermal barrier coatings. This study evaluated the effects of ceramic and metallic coating compositions and application processes on coatings microstructure and performance. The relative cyclic performance of the TBC systems was determined from the laboratory tests.


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