PSI - Issue 10

ScienceDirect Available online at www.sciencedirect.com Av ilable o line at ww.sciencedire t.com cienceDirect Structural Integrity Procedia 00 (2016) 000 – 000 Procedia Structural Integrity 1 8 91–96 Available online at www.sciencedirect.com ScienceDirect Structural Integrity Procedia 00 (2018) 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. © 2018 The Authors. Published by Elsevier Ltd. Thi is an open access article under the CC BY-NC-ND license (http://creativecommons.o g/licenses/by-nc-nd/3.0/) Peer-review under r sponsib lity of the scientific comm ttee of the 1st International Conference of the Greek Society of Experimental Mechanics of Materials. 1 st International Conference of the Greek Society of Experimental Mechanics of Materials Thermomechanical response of Fe 3 O 4 /PVDF nanocomposites A. Sanida a, *, Th.G. Velmachos a , S.G. Stavropoulos a , G.C. Psarras a , C. Tsonos b , A. Kanapitsas b , N. Soin c , E. Siores c a Smart Materials & Nanodielectrics Laboratory, Department of Materials Science,University of Patras, Patras 26504, Greece b Electronics Engineering Department, Technological Education Institute (TEI) of Sterea Ellada, 35100 Lamia, Greece c Institute for Materials Research and Innovation (IMRI), University of Bolton, Deane Road, BL3 5AB Bolton, UK Abstract Polyvinyledene fluoride (PVDF) is a semi-crystalline thermoplastic polymer use in various technol gi al pplications because of its enhanced thermal stability and good chemical resistance. Polymer matrix nanocomposites represent a novel and rapidly growing field of engineering materials due to their improved thermomechanical, electrical and magnetic performance. In the present study the thermomechanical behaviour and dielectric response of Fe 3 O 4 /PVDF nanocomposites is investigated varying the content of the reinforcing phase. © 2018 The Authors. Published by Elsevier Ltd. This is an open access article under the CC BY-NC-ND license (http://creativecommons.org/licenses/by-nc-nd/3.0/). Peer-review under responsibility of the scientific committee of the 1 st International Conference of the Greek Society of Experimental Mechanics of Materials Keywords: PVDF; iron oxide; dynamic mechanical behaviour; static mechnanical performance; dielectric properties; relaxations 1. Introduction Polymer matrix nanocomposites with embedded ceramic nanoparticles represent a novel class of engineering materials attracting the research interest of the scientific community (Schadler et al. (2007)). Ceramic nanoinclusions affect the electronic, electrical, magnetic, optical, thermal and mechanical performance of the nanocomposites opening o y the thermomech © 2018 The Authors. Pu by sev er td. responsibility of the scientific c t of the Greek oc y of Experimental Mechanics of Materi ). Ceramic nanoinclusions © 2016 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of PCF 2016.

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Keywords: High Pressure Turbine Blade; Creep; Finite Element Method; 3D Model; Simulation.

* Corresponding author. Tel.: +30 2610 969347; fax: +30 2610 969372. E-mail address: ksanida@upatras.gr Received: April 28, 2018; Received in revised form: July 21, 2018; Accepted: July 30, 2018

2452-3216 © 2016 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of PCF 2016. 2452-3216  2018 The Authors. Published by Elsevier Ltd. This is an open access article under the CC BY-NC-ND license (http://creativecommons.org/licenses/by-nc-nd/3.0/) Peer-review under responsibility of the scientific committee of the 1st International Conference of the Greek Society of Experimental Mechanics of Materials. 10.1016/j.prostr.2018.09.014 2452- 3216 © 2018 The Authors. Published by Elsevier Ltd. This is an open access article under the CC BY-NC-ND license (http://creativecommons.org/licenses/by-nc-nd/3.0/). Peer-review under responsibility of the scientific committee of the 1 st International Conference of the Greek Society of Experimental Mechanics of Materials t * Corresponding author. Tel.: +351 218419991. E-mail address: amd@tecnico.ulisboa.pt