PSI - Issue 2_B

ScienceDirect Available online at www.sciencedirect.com Av ilable o line at ww.sciencedire t.com ScienceDirect Structural Integrity Procedia 00 (2016) 000 – 000 Procedia Struc ural Integrity 2 (2016) 1692–1699 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 Introduction to the effect of the screening phenomenon of slip bands within grain microstructure Mohamed Ould Moussa a,b,* , Maxime Sauzay b a Pôle énergies renouvelables, Université Internationale de Rabat (UIR), Laboratoire des Energies Renouvelables et Matériaux Avancés (LERMA), Parc Technopolis Rabat-Shore, campus de l’UIR, Rocade Rabat-Salé, 11100, Rabat-Sala El Jadida, Morocco b CEA, DEN, DMN, SRMA, F-91191 GIF-SUR-YVETTE, FRANCE Abstract The aim of the current contribution is to compute grain boundary (GB) stress fields and fracture using respectively finite elements (FE) methods and analytical model in the case of several slip bands (SB) impinging the GB. Indeed, local plasticity in thin bands is largely observed during straining of polycrystals. For instance, channels (or clear bands) within grains are observed after post-irradiation tensile loading [Cui et al, 2013]. Slip bands thickness is about 50 nm which is about hundred times higher than the classical pile-up thickness. The intersection of such slip bands (SBs) with grain boundaries (GBs) can trigger microcracks initiation. Then, it is important to propose a fracture criterion for predicting GB microcracks nucleation as SBs impinge GB. Despite of many issuesdevelop pile-up based models of GB stress fields, observations showthat morethan single slip band are observed in real situation.Then, the main carried out tool is the analysis of the screening effects of SB on parameters of early validated single SB model. © 2016 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of ECF21. Keywords:Irradiated materials, Finite Fracture Mechanics, Grain boundaries, analytical criteria, strain localization, crystalline plasticity, slip bands int ractions, slip ands screeni g finite elements (FE) methods and anal (SB) impinging Peer-review under responsibility of t Copyright © 2016 The Auth rs. Published by Elsevier B.V. This is an open access articl u der the CC BY-NC-ND license (http://creativecommons.org/ icenses/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.

* Corresponding author: Mohamed Ould Moussa. Tel.: +212 530104111; fax: +212 530103030. E-mail address: Mohamed.ouldmoussa@uir.ac.ma

* 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.

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.2016.06.214