PSI - Issue 2_A

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ScienceDirect

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 Struc ural Integrity 2 (2016) 2291–2298 Structural Integrity Procedia 00 (2016) 000–000 tr t r l I t rit r i ( )

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21st European Conference on Fracture, ECF21, 20-24 June 2016, Catania, Italy

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. Effect of surface modification on the stability of oxide scales formed on TiAl intermetallic alloys at high temperature D.Pilone*, A.Brotzu, F.Felli Dipartimento ICMA, Sapienza Università di Roma, Via Eudossiana 18, 00184 Roma, Italy TiAl intermetallic alloys have many interesting potential applications in the automotive and aerospace industry due to their low density and good mechanical properties at high temperature. Unfortunately they have a low oxidation resistance at temperature higher than 700 °C and the improvement of their oxidation behavior is still an open issue. In this work the surface of a TiAlCrNb alloy has been modified by means of either anodic coating or cerium conversion coating. Afterwards the stability of the oxide scale formed at 900 °C has been studied by analyzing crack formation and propagation, which is the phenomenon that can produce s ale spallation during the alloy cooling. © 2016 The Authors. Published by Elsevier B.V. Pe r-review under res onsibility of the Scientific Committee of ECF21. Keywords: TiAl intermetallics; oxidation; surface modification. 1. Introduction TiAl intermetallic alloys are v ry promisi g structural materials for aeroengine and automotive applications because of their low density coupled with good mechanical properties at high temperature. However, these alloys are not industrially used ecause of their low fracture toughness at room temperature and low oxidation resistance at elevated temperatures. One of the viable solutions for improving the oxidation resistance of TiAl alloys is alloying with ternary, quaternary or more elements such as Cr, Nb, Si and W, as described by Haanappel et al. (2002), Pilone et al. (2012), Pilone et al. (2013) and Kim et al. (2014). The most important problem related to this method is that in i ti t I , i i it i , i i , , It l i l i t t lli ll i t ti t ti l li ti i t t ti i t t t i l it ood mechanical properties at high temperature. Unfortunately they have a low oxidation resistance at temperature i t t i t t i i ti i i till i . t i t i l ll i i it i ti i i ti . t t t ilit t i l t t i l i ti ti , i i t t t l ll ti i t ll li . © 2016 The t . ublished by Elsevier B.V. Pe r-r v ew u i ilit t Scientifi o itt . : i l i t r t lli ; i ti ; rf ifi ti . 1. In i i l i t t lli ll i i t t l t i l i t ti li ti t i l it l it i l ti t i t t . , t ll t i t i ll t l t t t t t l i ti i t t l t t t . t i l l ti i i t i ti i t i l ll i ll i it t , t l t , , i , i l t l. , il et al. (2012), Pilone et al. (2013) i t l. . t i t t l l t t t i t i t t i 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. © 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. Abstract

* Corresponding author. Tel.: +390644585879; fax: +390644585641. E-mail address: daniela.pilone@uniroma1.it i t r. l.: ; f : . - il : i l . il ir .it rr

* 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. l i r . . i i ilit t i tifi C itt . - t r . li

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.2016.06.287