PSI - Issue 2_A

ScienceDirect Available online at www.sciencedirect.com Av ilable o line at ww.sciencedire t.com Sci ceDirect Structural Integrity Procedia 00 (2016) 000 – 000 Procedia Structu al Integrity 2 (2016) 112–119 Available online at www.sciencedirect.com ScienceDirect Structural Integrity Procedia 00 (2016) 000 – 000 il l li i i t t l t it i

www.elsevier.com/locate/procedia . l i . /l t / i

www.elsevier.com/locate/procedia

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 Feasibility study of adhesive bonding reinforcement by electrospun nanofibers F. Musiari 1 *, A. Pirondi 1 , F. Moroni 1 , G. Giuliese 2 , J. Belcari 2 , A. Zucchelli 2 , T. M. Brugo 2 , G. Minak 2 , C. Ragazzini 2 1 Dipartimento di Ingegneria Industriale, Università di Parma Parco Area delle Scienze 181/A, 43124 Parma, Italy web page: http://www.unipr.it 2 Dipartimento di Ingegneria Industriale, Alma Mater Studiorum - Università di Bologna viale del Risorgimento 2, 40136 Bologna, Italy web page: http://www.unibo.it In previous works, the authors showed that the interleaving of an lectrospun nylo nanofibrous t at the interface between adjacent plies of a composite laminate increases the delamination strength. In particular, the nanomat acts a n t-like reinforci g web, enabling a ply-to-ply bridging effect. This rei forcing property of the nanomats can be pot ntially used in other applications which need to impr ve the fracture resistance of interfa es, uch as adhesive bonding. The present work an lyses th feasibility of an electrospun polymeric nanomat as adhesive carrier n reinforcing web in i dustrial bonding. Thus the adhesive is used to pre-impregnate a nylon n ofibrous mat that is then placed at the interface between two metal pieces then cured. The aim of the work is first to ssess the effectiveness of this procedure, by comparison of the mode-I fracture toughness measured with DCB (Do ble Cantilever Beam) tests with and wit out the reinforcement in t e adhesive layer. For this purpose, a 2024-T3 aluminum alloy will be bonded using a general purpose, one-part epoxy resin with low viscosity. Giuliese , J. Be 1 i ti t i i t i l , i it i ll i / , , t l tt // . i .it i ti t i i t i l , l t t i i it i l i l l i t , l , t l tt // . i .it , . , , . , . . . , . , , . 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. © 2016 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of ECF21. ity o th . Abstract . . .

Keywords: High Pressure Turbine Blade; Creep; Finite Element Method; 3D Model; Simulation. Keywords: electrospun nanofiber mats, bonding reinforcement, Mode I fracture toughness, adhesive carrier i t , i i t, t t , i i l t

* Corresponding author. Tel.: +393331296018 E-mail address: francesco.musiari@studenti.unipr.it i t . l.: il . i i t ti. i .it

* 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 . . . t . 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.2016.06.015