PSI - Issue 13

ScienceDirect Available online at www.sciencedirect.com Av ilable o line at ww.sciencedire t.com Sci ceDirect Structural Integrity Procedia 00 (2016) 000 – 000 Procedia Structural Integrity 13 (2018) 1226–1231 Available online at www.sciencedirect.com ScienceDirect Structural Integrity Procedia 00 (2018) 000 – 000 Available online at www.sciencedirect.com ScienceDirect Structural Integrity Procedia 00 (2018) 000 – 000

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XV Portuguese Conference on Fracture, PCF 2016, 10-12 February 2016, Paço de Arcos, Portugal Thermo-mechanical modeling of a high pressure turbine blade of an airplane gas turbine engine P. Brandão a , V. Infante b , A.M. Deus c * a Department of Mechanical Engineering, Instituto Superior Técnico, Universidade de Lisboa, Av. Rovisco Pais, 1, 1049-001 Lisboa, Portugal b IDMEC, Department of Mechanical Engineering, Instituto Superior Técnico, Universidade de Lisboa, Av. Rovisco Pais, 1, 1049-001 Lisboa, Portugal c CeFEMA, Department of Mechanical Engineering, Instituto Superior Técnico, Universidade de Lisboa, Av. Rovisco Pais, 1, 1049-001 Lisboa, Portugal Abstract During their operation, modern aircraft engine components are subjected to increasingly demanding operating conditions, especially the high pressure turbine (HPT) blades. Such conditions cause these parts to undergo different types of time-dependent degradation, one of which is creep. A model using the finite element method (FEM) was developed, in order to be able to predict the creep behaviour of HPT blades. Flight data records (FDR) for a specific aircraft, provided by a commercial aviation company, were used to obtain thermal and mechanical data for three different flight cycles. In order to create the 3D model needed for the FEM analysis, a HPT blade scrap was scanned, and its chemical composition and material properties were obtained. The data that was gathered was fed into the FEM model and different simulations were run, first with a simplified 3D rectangular block shape, in order to better establish the model, and then with the real 3D mesh obtained from the blade scrap. The overall expected behaviour in terms of displacement was observed, in particular at the trailing edge of the blade. Therefore such a model can be useful in the goal of predicting turbine blade life, given a set of FDR data. ECF22 - Loading and Environmental effects on Structural Integrity A study on failure of double-layer thermal barrier coatings subjected to uniaxial c mpression tests using acoustic emission analysis and digital image correlation Marcel Adam a , Christian Kontermann a , Matthias Oechsner a * a Chair and Institute for Materials Technology, Technical University Darmstadt, Grafenstr. 2, 64283 Darmstadt, Germany Abstract The failure behavior and fracture process of double-layer thermal barrier coatings under uniaxial compressive substrate loading has been investigated. Coating systems containing GZO with low and high porosity (LP, HP) were fabricated to examine the influence of microstructure on failure behavior and strain energy. An YSZ-HP single-layer system serves as a reference. All ceramic coatings were deposited via atmospheric plasma spraying (APS) on cylindrical rods and turbine blade-shaped specimens made from CoNiCrAlY (LCO-22) coated, nickel-based, single crystal superalloy (PWA 1483). Prior to compression tests, isothermal pre-oxid tion at 1050 °C and dwell-times of 100, 500 and 1.500 hours, as well as cyclic annealing tests between 50 and 1050 °C up to 500 cycles were performed, to study the effects of thermal ageing on strain energy to failure. In-situ acoustic emission (AE) measurements pr vides quantitative info mation about the failure processes un er comp s ve substrate loading. A stereo camera system moni ors the thr e-dimensional displacem nts and the surface fracture processes. For as-spray d coating , strain to failure of the investigated GZO/YSZ systems is c mparable to the referenced single-layer TBC. AE analysis indicates coating failure at earlier stages and less substrate loads after thermal ageing with increasing dwell-time. Consequently, the pre-oxidation leads to reduced strain to failure values in all investigated coating systems. Digital image correlations (DIC) suggests that the failure behavior of as-sprayed GZO/YSZ coatings is similar to the referenced YSZ system. However, a different behavior was observed for pre-oxidized coatings, where cracking and spallation of GZO occurs predominantly. © 2018 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the ECF22 organizers. ECF22 - Loading and Environmental effects on Structural Integrity A study on failure of double-layer thermal barrier coatings subjected to uniaxial compression tests using acoustic emission analysis and digital image correlation Marcel Adam a , Christian Kontermann a , Matthias Oechsner a * a Chair and Institute for Materials Technology, Technical University Darmstadt, Grafenstr. 2, 64283 Darmstadt, Germany Abstract The failure b havior and fracture process of double-layer thermal barrier coatings under uniaxial compressive substrate loading has been investigated. Coati g syst ms contai ing GZO with low and high porosit (LP, HP) wer fabricated to examine the influence of microstructure on failure behavior and st in energy. An YSZ-HP single-layer system serves as a reference. All ceramic c atings were deposited via atmospheric plasma spraying (APS) on cy indrical rods and turbine blade-shaped specimens made from CoN CrAlY (LCO-22) coated, nickel-based, single crystal superalloy (PWA 1483). Prior to compression tests, isothermal pre- xidation at 1050 °C and dwell-times of 100, 500 and 1.500 hours, as well as cyclic annealing tests between 50 and 1050 °C up to 500 cycles w e perfor ed, to study he effects f thermal ageing on strain energy to failure. In-situ acoustic emissio (AE) measuremen s provides quantitative information about the failure processes under ompressive substrate l ad . A ster o came a syst m monitors the three-dimen ional displaceme ts and the surfa fractur processes. For as-sprayed c atings, strain to failure of th inv stigated GZO/YSZ systems is comparable to the refere ed i le-layer TBC. AE analysis indicates coating failure at earlier stages and less substrate loads after ther al ageing with increas ng dwell-time. Consequently, the pr -oxid tion le ds to r duced strain to failure values in all investigated coating syst ms. Digital image correlations (DIC) suggests that the failure behavior of as-sprayed GZO/YSZ coatings is imi r to the referenced YSZ system. However, a different behavior was observed for pre-oxidized coatings, where cracking and spallation of GZO occurs predominantly. © 2018 The Authors. Publ shed by Elsevier B.V. Peer-review under responsibility of the ECF22 organizers. © 2016 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of PCF 2016. Keywords: gadolinium zirconate; double-layer; thermal barrier coating; acoustic emission; digital image correlation Keywords: gadolinium zirconate; double-layer; thermal barrier coating; acoustic emission; digital image correlation © 2018 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the ECF22 organizers.

Keywords: High Pressure Turbine Blade; Creep; Finite Element Method; 3D Model; Simulation.

* Corresponding author. Tel.: +49 6151 16-25119; fax: +49 6151 16-25122. E-mail address: adam@mpa-ifw.tu-darmstadt.de * Correspon ing author. Tel.: +49 6151 16-25119; fax: +49 6151 16-25122. E-mail address: adam@mpa-ifw.tu-darmstadt.de

* Corresponding author. Tel.: +351 218419991. E-mail address: amd@tecnico.ulisboa.pt 2452 3216 © 2018 Th Authors. Published by Elsevie B.V. Peer-review under responsibility of the ECF22 organizers. 2452-3216 © 2018 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the ECF22 organizers.

2452-3216 © 2016 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of PCF 2016.

2452-3216  2018 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the ECF22 organizers. 10.1016/j.prostr.2018.12.252