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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. Copyright © 2017 The Authors. Published by Elsevier B.V. This is an open access article under the CC BY-NC-ND license (http://crea ivecommons.org/licenses/by-nc-nd/4.0/). Peer-review under responsibility of the Scientific Committee of IGF Ex-Co. XXIV Italian Group of Fracture Conference, 1-3 March 2017, Urbino, Italy Study of defe t formation in Al 7050 alloys A.Brotzu*, G.De Lellis, F.Felli and D.Pilone Dip. ICMA, Sapienza Università di Roma, Via Eudossiana 18, Roma Abstract The Al 7050 alloy is an Al-Zn-Mg-Cu-Zr alloy having good mechanical properties. This alloy has been developed in order to overcome stress corrosion cracking problems that characterise 7xxx Al alloys. Despite Al 7050 is widely used for aerospace applications, it can be subjected to crack initiation and propagation during the manufacturing process. In this work cracked Al 7050 components have been analysed in order to identify possible causes of crack formation such as coarse intermetallic phase presence, voids or wrong mechanical machining processes. © 2017 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of IGF Ex-Co. Keywords: Aluminium alloys, Al 7050, Fracture. 1. Introduction Over the last decades many efforts have been spent to realise newer aluminium alloys and to improve the performances of the existing ones in order to find, for Al 7XXX alloys, new application fields as said by J.C. Williams et al. (2003). The Al 7XXX mechanical properties are affected by the alloy chemical composition and by the alloy microstructure related to the used production process parameters. Among the different Al alloys we are going to focus on the Al 7050. Aluminium alloy 7050 is an aerospace grade of aluminium characterised by high strength, stress cor o i cracking r sista ce and toughness as described by M. Dixit et al. (2008). It is particularly suited for heavy plate applications due to its lower quench sensitivity and retention of strength in thicker sections. Al 7050 therefore is the premium choice aerospace aluminium for applications such as fuselage frames, bulkheads and wing skins. Aluminium alloys based on the Al-Zn-Mg composition can be heat treated and age hardened in different XXIV Italian Group of Fracture Conference, 1-3 March 2017, Urbino, Italy Study of defect formation in Al 7050 alloys A.Brotzu*, G.De Lellis, F.Felli and D.Pilone Dip. ICMA, Sapienza Università di Roma, Via Eudossiana 18, Roma Abstract The Al 7050 alloy is an Al-Zn-Mg-Cu-Zr alloy having good mechanical properties. This alloy has been developed in order to ov rcome stress corrosi n crackin probl ms that characterise 7xxx Al alloys. Despite Al 7050 is widely used for aerospace application , it can be subjected to crack initia ion and propagation during the manufacturing process. In this work cracked Al 7050 components have been analysed in order to ide tify possible causes of crack formatio such a coarse intermetalli phase presence, v ids or wrong mechanical machining processes. © 2017 The Authors. Published by Elsevier B.V. Peer-review under espons bility of the Scientific Committee of IGF Ex-Co. Keywords: Aluminium alloys, Al 7050, Fracture. 1. Introduction Over the last decades many efforts have been spent to realise newer aluminium alloys and to improve the performanc s of the exi ting ones in order to fi d, for Al 7XXX alloys, new application fields as said by J.C. Willia s et al. (2003). The Al 7XXX mechanical properties are affected by the alloy hemical composition and by the alloy microstructure related to the used production process param ters. Among the different Al alloys we are going to focus on the Al 7050. Aluminium all y 7050 is an aerospac grade of aluminium characterised by high stre th, str s cor osion cracking resistance and toughne s as described by M. Dixit et al. (2008). I is particularly uited for h avy plate applica io s due to i s lower q ench sen itivity an retention of strength in thicker sec ons. Al 7050 the efore is the prem um choice aero pace alumi ium for applications such as fus la e frames, bulkheads and wing skins. Aluminium alloys based on the Al-Zn-Mg co p sition can be heat tre ted and age hardened in differe t © P © 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.

* Corresponding author. Tel.: +390644585650. E-mail address: andrea.brotzu@uniroma1.it * Corresponding author. Tel.: +390644585650. E-mail address: andrea.brotzu@uniroma1.it

* Corresponding author. Tel.: +351 218419991. E-mail address: amd@tecnico.ulisboa.pt 2452-3216 © 2017 The Authors. Published by Elsevier B.V. Peer-review und r responsibil ty of the Scientific Committee of IGF Ex-Co. 2452-3216 © 2017 The Authors. Published by Elsevier B.V. Peer review under r sponsibility of the Scientific Committee of IGF Ex-Co.

2452-3216 © 2016 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of PCF 2016. Copyright © 2017 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 IGF Ex-Co. 10.1016/j.prostr.2017.04.015