PSI - Issue 2_A

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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 Fracture toughn ss determination by repetitive n no-imp ct testing in Cu/W nanomultilayers with length-scale-dependent films properties E. F utos a *, M. Karlik b , T. Polcar a,c a Department of Control Engineering, Faculty of Electrical Engineering, Czech Technical University in Prague, Technická 2, Prague 6, Czech Republic. b Department of Materials, Faculty of Nucl a Sciences and Physical Engineering, Czech Technical University in Prague, Trojanova 13, 120 00 Prague 2, Czech Republic . c National Centre for Advanced Tribology (nCATS), University f Southampton, University Road, Southampton SO17 1BJ UK . Abstract Nanoscale metallic multilayers based on Cu/W have been considered as a potential material for structural applications in nuclear reactors and fo the cladding of storage tanks for advanced fu ls kept at high mperatures. The und rstanding f how me han cal properties change in relation to periodicity,  , is required in order to use Cu/W nano-multilayers as a protective coating agai st radiation damage. The aim of this work is to demons rate the f asibility of using the repetitive-nano-impact technique to btain quantitative fracture toughness, K C , values in nano-multilayers and assess its variation as a functi n of  . © 2016 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of ECF21. Keywords: Dynamic fracture; Fracture toughness; Layered material; Impact testing; Stress intensity factor. 1. Introduction Nanoscale metallic multilayers (NMMs) represent a new class of engineering materials consisting of alternating nanoscale multilayers of two different metals. These systems have been studied intensively during the last 10 years for many applications due to their exceptional mechanical properties. Examples of their unique properties are hardness enhancement (Misra et. al., 2005) and anomalous modulus compared with monolithic coatings of the constituent 21st European Conference on Fracture, ECF21, 20-24 June 2016, Catania, Italy Fracture toughness determination by repetitive nano-impact testing in Cu/W nanomultilayers with length-scale-dependent films properties E. Frutos a *, M. Karlik b , T. Polcar a,c a Department of Control Engineering, Faculty of Electrical Engineering, Czech Technical University in Prague, Technická 2, Prague 6, Czech Republic. b Department of Materials, Faculty of Nuclear Sciences and Physical Engineering, Czech Technical University in Prague, Trojanova 13, 120 00 Prague 2, Czech Republic . c National Centre for Advanced Tribology (nCATS), University of Southampton, University Road, Southampton SO17 1BJ UK . Abstract Nanoscale metallic multilayers based on Cu/W have been considered as a potential material for structural applications in nuclear re ctors and for the cladding of storage tanks for dvanced fuels kept at high t mperatur s. The understanding of how mechanic l prope ties c ange in relation t pe iodi ity,  , is r quire in order to use Cu/W nano-multilayers as a protective coating aga nst radiation damage. T e aim of his work is to demonstrate the feasibility of sing the repetitiv -nano-impact t chnique to obtain quantit tive fr cture toughness, K C , value in nano-multilayers and assess its variation as function of  . © 2016 Th Authors. Published by Elsevier B.V. Peer-review under esponsibility of the Scientific Committee of ECF21. Keywords: Dynamic fracture; Fracture toughness; Layered material; Impact testi g; Stress i tensity f ct r. 1. Introduction Nanoscale metallic multilayers (NMMs) represent a new class of engineering materials consisting of alternating nanoscale multilayers of two different metals. These syst ms h ve be studied intensive y during the last 10 years for many application due to their xceptional mechanical properties. Exa ples of th ir unique p oper i s re hardnes enhancement (M sra et. al., 2005) and anomalous modulus compared with monolithic coatings of the constitu nt 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.

* 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 ECF21. * Corresponding author. Tel.: 00420 224357598. E-mail address: frutoemi@fel.cvut.cz * Corresponding author. Tel.: 00420 224357598. E-mail address: frutoemi@fel.cvut.cz

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.2016.06.177