PSI - Issue 2_B

ScienceDirect Available online at www.sciencedirect.com Av ilable o line at www.sciencedire t.com ienceDirect Structural Integrity Procedia 00 (2016) 000 – 000 Procedia Structu al Integrity 2 (2016) 597–603 Available online at www.sciencedirect.com ScienceDirect Structural Integrity Procedia 00 (2016) 000–000 Available online at www.sciencedirect.com ScienceDirect Structural Integrity Procedia 00 (2016) 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. 21st European Conference on Fracture, ECF21, 20-24 June 2016, Catania, Italy Mechanical properties degradation of (Al-Cu-Li) 2198 alloy due to corrosion exposu e Nikolaos D. Alexopoulos a, *, Angeliki Proiou a , Wolfgang Dietzel b , Carsten Blawert b , Volker Heitmann b , Mikhail Zheludkevich b , Stavros K. Kourkoulis c a Department of Financial Engineering, University of the Aegean, 82 132 Chios, Greece b Institute of Materials Research, Department of Corrosion and Surface Technology, Helmholtz-Zentrum Geesthacht, 21502 Geesthacht, Germany c Lab of Testing and Materials, Dept of Mechanics, National Technical University of Athens, 9 H roe Polytechniou Str., 15773 Athens, Greece Abstract The present work investigates the corrosion resistance of the innovative Al-Cu-Li (2198) aluminum alloy; a comparison against Al-Cu (2024) alloy is attempted. Tensile specimens were pre-corroded for different exposure times to exfoliation corrosion solution and immediately afterwards they were tested in tension. For small exposure times (< 12 h) small pits could be found on the corroded surfaces; pitting was also noticed at the small side surfaces (thickness) of the tensile specimens. Corrosion exposure seems not to essentially decrease the yield stress of AA2198 even for high exposure times, while this was not the case for AA2024. After heavy corr sion exposure (>12 h), AA2024 lost almost 30% of its initial ultimat tensile strength, while for AA2198 the respective value was only 11%. Al-Cu-Li alloy shows superior corrosion resistance in terms of maintaining higher percentages of tensile ductility; AA2198 exhibited higher remaining elongation at fracture values due to corrosion degradation for all investigated exposure times. © 2016 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of ECF21. Keywords: alloy 2024; alloy 2198; tension; artificial ageing; exfoliation corrosion; ductility 21st European Conference on Fracture, ECF21, 20-24 June 2016, Catania, Italy Mechanical properties degradation of (Al-Cu-Li) 2198 alloy due to corrosion exposure Nikolaos D. Alexopoulos a, *, Angeliki Proiou a , Wolfgang Dietzel b , Carsten Blawert b , Volker Heitmann b , Mikhail Zheludkevich b , Stavros K. Kourkoulis c a Department of Financial Engi eering, University of the Aegean, 82 132 Chio , Greece b Institute of Materials R se rch, Departm nt of Co rosion nd Surfa e Technolog , Helmholtz-Zent m Gees hacht, 21502 Geesthac t, Germany c Lab of Testing and Materials, Dept of Mechanics, National Technical University of Athens, 9 Heroes Polytechniou Str., 15773 Athens, Greece Abstract The present work investigates the corrosion r s sta ce of the innovativ Al-Cu-Li (2198) aluminum alloy; a c mparison against Al-Cu (2024) alloy is attempted. Tensile sp cimens were pre-cor oded for different xposure times to exfoliation c rrosi solution n immediately afterwards they w re est d in tension. For small expo ure tim s (< 12 h) small pits could be found on th corr ded surfaces; pitting was also noticed at the small side surfaces (thickness) of the tensile specimens. Corrosi n exposure seems ot to ssentially decrease the yield stress of AA2198 ven for high exposure times, while this w s not the case for AA2024. After heavy corrosion exposure (>12 h), AA2024 lo t almost 30% of its in ti l ult mate tensile strength, while for AA2198 the r spective value was only 11%. Al-Cu-Li alloy shows superior corrosion resistance in t rms of maintaining higher perce tages of tensile ductility; AA2198 exhibited higher remaining elongation at fracture values due to corrosion degradation for all investigated exposure times. © 2016 The Autho s. Publ shed by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of ECF21. Copyright © 2016 The Authors. Published by El evier B.V. This is an open access article u der the CC BY-NC-ND licen e (http://creativec mmons.org/licenses/by-nc-nd/4.0/). Peer-review under responsib lity of the Scientific Committee of ECF21.

© 2016 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of PCF 2016. Keywords: alloy 2024; alloy 2198; tension; artificial ageing; exfoliation corrosion; ductility

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

* Corresponding author. Tel.: +351 218419991. E-mail address: amd@tecnico.ulisboa.pt 2452 3216 © 2016 Th Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of ECF21. 2452-3216 © 2016 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of ECF21. * Correspon ing author. Tel.: +0030-22710-35464; fax: +0030-22710-35429. E-mail address: nalexop@aegean.gr * Corresponding author. Tel.: +0030-22710-35464; fax: +0030-22710-35429. E-mail address: nalexop@aegean.gr

2452-3216 © 2016 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of PCF 2016. Copyright © 2016 The Authors. Published by Elsevier B.V. This is an open access article under the CC BY-NC-ND license ( http://creativecommons.org/licenses/by-nc-nd/4.0/ ). Peer review under responsibility of the Scientific Committee of ECF21. 10.1016/j.prostr.2016.06.077