PSI - Issue 2_A

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 Struc ural Integrity 2 (2016) 3272–3279 Available online at www.sciencedirect.com ScienceDirect Structural Integrity Procedia 00 (2016) 000–000 il l li t . i i t. Structural I te rit r i ( )

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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 Fatigue crack growth behaviour of the 6082-T6 aluminium using CT specimens with distinct notches José A.F.O. Correia a *, Abílio M.P. De Jesus a , Ana S.F. Alves a , Grzegorz Lesiuk b , Paulo J.S. T vares a , Pedro M.G.P. Moreira a a INEGI/Faculty of Engineering, University of Porto, Rua Dr. Roberto Frias, 4200-465 Porto, Portugal. b Faculty of Mechanical Engineering, W oc ł aw University of Tech ology, Smoluchowskiego 25, 50-370 Wroc ł aw, Poland. Abstract This paper presents a study aiming at characterizing the fatigue crack growth behaviour of the 6082-T6 aluminium alloy using standard CT specimens. The fatigue crack growth threshold is also characterized according to the ASTM E 647 standard. Besides the standard CT specimens with sharp notches, specimens with initial circular notches were also fatigue tested. The threshold stress intensity factor ranges, Δ K th , are compared for the distinct notches under study. The fatigue crack propagation rate in the regime II are obtained using the Paris law. A comparison is made between the CT specimens geometries with distinct notches under consideration. The Δ K th values for the geometry of standard CT specimens present lower values when compared with the geometry of the CT specimens with blunted notches. © 2016 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of ECF21. Keywords: Type your keywords here, separated by semicolons ; 1. Introduction The characterization of the fatigue rack propagation rates in metallic materials and aluminum alloys is of high importance. More importantly, the fatigue crack growth rates and threshold values of the stress intensity factor ranges for distinct notches are of primordial importance. Generally the structural details have different geometries, then it becomes necessary to study the fatigue crack growth covering such geometric configurations. The current study aims at assessing the crack growth behavior of the 6082-T6 aluminium alloy using CT specimens with distinct notch geometries. To this end, the ASTM E 647 standard is used in order to obtain the Δ K th values and the properties of the fatigue crack propagation rates in the regime II, using the Paris law (Paris et al. (1963)). The mechanical and chemical properties for 6082-T6 aluminum alloy (Moreira et al. (2008, 2009)) are also presented. a es a a a I I/ lt f i i , i sity of Porto, Rua Dr. Rob t i , - t , t l. b lt f i l i i , ł i it f l , l i , - ł , l . Abstract i t t i i t t i i t ti t i t l i i ll i t i . ti t t l i l t i i t t t . i t t i it t , i it i iti l i l t l ti t t . t l t i t it t , t , t i ti t t t . ti ti t i t i t i i t i l . i i t t i t i it i ti t t consideration. t l t t t i t l l it t t t i it l t t . © 2016 The Authors. Publishe l i . . Peer-review under responsibility of the Scientific C itt . : r r r , r t i l ; . i t i ti t ti ti t i t lli t i l l i ll i i i t . i t tl , t ti t t t l l t t i t it t i ti t t i i l i t . ll t t t l t il i t t i , t it t t t ti t i t i i ti . t t i t i t t i t l i i ll i i it i ti t t t i . t i , t t i i t t i t t l t ti t ti ti t i t i , i t i l i t l. . Copyright © 2016 The Authors. Publishe by Elsevier B.V. This is an open access rticl under the CC BY-NC-ND license (http://creativecommons. rg/lice ses/by-nc- /4.0/). Peer-review under responsibility 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: High Pressure Turbine Blade; Creep; Finite Element Method; 3D Model; Simulation.

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* Corresponding author. Tel.: +351 218419991. E-mail address: amd@tecnico.ulisboa.pt 2452-3216 © 2016 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of ECF21. - t r . li l i r . . i i ilit t i ti i itt .

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.2016.06.408