Failure Mechanisms of APS-YSZ-CoNiCrAlY Thermal Barrier Coating Under Isothermal Oxidation and Solid Particle Erosion
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Failure Mechanisms of APS-YSZ-CoNiCrAlY Thermal Barrier Coating Under Isothermal Oxidation and Solid Particle Erosion Samia K. Essa1 • Kuiying Chen2 • Rong Liu1 • Xijia Wu2 • Matthew X. Yao3
Submitted: 22 May 2020 / in revised form: 15 October 2020 / Accepted: 9 November 2020 ASM International 2020
Abstract The high-temperature oxidation and solid particle erosion of thermal barrier coating (TBC) system which consists of a 8 wt.% yttria-partially stabilized zirconia (YSZ) top coat and CoNiCrAlY bond coat deposited on Inconel 718 substrate via air plasma spraying (APS) process are studied experimentally. Isothermal oxidation tests of the APS-TBCs are conducted at 1050, 1100 and 1150 C in air for up to 1970 h. Solid particle erosion tests are also performed on both as-deposited and heat-treated APS-TBC specimens at selected particle impingement angles and velocities in room temperature. The scanning electron microscopy (SEM) analyses of the cross sections of the APS-TBC specimens after the oxidation tests show the formation of thermally grown oxide (TGO) scale due to the oxidation of CoNiCrAlY bond coat, and the oxidation kinetics of TGO growth is described by the parabolic rate equation. The failure of the APS-TBC system under isothermal oxidation is associated with the spallation of the top coat through propagation and coalescence of cracks along the coating interface, which is affected by the TGO growth. The solid particle erosion rate of the top coat is found to increase with impingement angle and reach the maximum erosion rate at normal impingement of particles. The erosion resistance of the APS-TBC is observed to increase after the APS-TBC specimen has been exposed at & Rong Liu [email protected] 1
Department of Mechanical and Aerospace Engineering, Carleton University, Ottawa, Canada
2
Structures, Materials and Performance Laboratory, Aerospace Research Center, National Research Council Canada, Ottawa, Canada
3
Kennametal Stellite Inc., Belleville, Canada
1100 and 1150 C for 72 h, probably due to the sintering effect on the top coat, which results in reduction of top coat porosity. Keywords thermal barrier coating (TBC) thermally grown oxide (TGO) isothermal oxidation solid particle erosion crack
Introduction Due to excellent mechanical properties and resistance to high-temperature inelastic deformation, nickel-based superalloys have long been used as the base alloys for turbine blades operating at high temperatures close to their melting point (Ref 1). For decades, efforts have been made to further increase the inlet temperature of engines by using thermal barrier coatings (TBCs) deposited on external surface of turbine blades so as to protect the substrates from high-temperature attack and corrosion, thus extending the service life of the blades (Ref 2). The current state-ofthe-art TBC systems are made of yttria-stabilized zirconia (YSZ) deposited either by air plasma spray (APS) or electron beam-physical vapor deposition (EB-PVD) process, with applying platinum modifie
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