PSI - Issue 10

ScienceDirect Available online at www.sciencedirect.com Av ilable o line at ww.sciencedire t.com ienceDirect Structural Integrity Procedia 00 (2016) 000 – 000 Procedia Structural Integrity 1 8 79–84 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. © 2018 The Authors. P blished by Elsevier Ltd. This is an open access article under the CC BY-NC-ND license (http://creativecommons.org/licenses/by-nc-nd/3.0/) Peer-review under responsibility of the scientific committee of the 1st International Conference of the Greek Society of Experimental Mechanics of Materials. 1 st International Conference of the Greek Society of Experimental Mechanics of Materials Effect of corrosion exposure on aluminum alloy 2024 for different artificial ageing conditions N. Siskou a , Ch. Charalampidou a , N.D. Alexopoulos a, *, S.K. Kourkoulis b a Department of Financial Engineering and Management, School of Engineering, University of the Aegean, 82 132 Chios, Greece b 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 behaviour of AA2024 in two different conditions, named T3 and Peak-Ageing (PA), respectively. Tensile specimens were artificially aged up to the PA condition, subsequently corroded for different exposure times to exfoliation corrosion solution and then they were immediately tensile tested. The corrosion exposure seems to essentially affect the mechanical behaviour of the specimens in T3 condition while this was not the case for the specimens in PA condition. After only 2 h corrosion exposure time, almost 23 % decrease in elongation at fracture for AA2024-T3 was noticed, while less than half of this decrease was evident in the PA condition for the same corrosion exposure. For higher exposure times (> 24 h), specimens at PA condition exhibi ed lower corrosion-induced de rease in tensile ductility, thus implying that surface deterioration mechanism chang with artificial ag ing of heat-treatable aluminium all ys. © 2018 The Aut ors. Published by Elsevier Ltd. This is an open access article under the CC BY-NC-ND license (http://creativecommons.org/licenses/by-nc-nd/3.0/). Peer-review under responsibility of the scientific committee of the 1 st International Conference of the Greek Society of Experimental Mechanics of Materials Keywords: Aluminum alloys; corrosion; ageing; tension; yield stress ga t uthors. Publish en access article under the r- i t

1. Introduction

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

Keywords: High Pressure Turbine Blade; Creep; Finite Element Method; 3D Model; Simulation. Aluminium alloys from 2xxx series are commonly used in the aviation industry due to their high specific mechan ical pr perties and damage toler nce ca abil ies and attributed this high perf rmance to their complex microstructure

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* Corresponding author. Tel.: +30 22710 35464; fax: +30 22710 35429. E-mail address: nalexop@aegean.gr Received: May 22, 2018; Received in revised form: July 30, 2018; Accepted: July 06, 2018

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 Ltd. This is an open access article under the CC BY-NC-ND license (http://creativecommons.org/licenses/by-nc-nd/3.0/) Peer-review under responsibility of the scientific committee of the 1st International Conference of the Greek Society of Experimental Mechanics of Materials. 10.1016/j.prostr.2018.09.012 2452- 3216 © 2018 The Authors. Published by Elsevier Ltd. This is an open access article under the CC BY-NC-ND license (http://creativecommons.org/licenses/by-nc-nd/3.0/). Peer-review under responsibility of the scientific committee of the 1 st International Conference of the Greek Society of Experimental Mechanics of Materials t * Corresponding author. Tel.: +351 218419991. E-mail address: amd@tecnico.ulisboa.pt