PSI - Issue 2_A

ScienceDirect Available online at www.sciencedirect.com Av ilable o line at ww.sciencedire t.com Scie ceDirect Structural Integrity Procedia 00 (2016) 000 – 000 Procedia Structu al Integrity 2 (2016) 452–459 Available online at www.sciencedirect.com ScienceDirect Structural Integrity Procedia 00 (2016) 000–000 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 A cohesive finite element model based ALE formulation for z-pins reinforced multilayered composite beams Marco Francesco Funari, Fabrizio Gr co, Paolo Lonetti* Department of Civil Engineering, University of Calabria, Via P. Bucci, Cubo39B, 87030, Rende, Cosenza, Italy. Abstract A computational formulation able to simulate fast crack growth in multilayered composite reinforced with z-pins is proposed. In particular, in order to identify the initiation and the growth of the crack, a moving mesh strategy, based on ALE approach, is combined with a cohesive methodology, in which weak based moving connections with the boundary adjoining layers are implemented by using a finite element formulation. Contrarily, z-pin reinforced area was simulated with a deformation of a set of discrete nonlinear springs fixed to material domain. Despite existing methodologies available from the literature, the present paper proposes a computational procedure able to study the dynamic crack growth in composite structures with a relatively low computational efforts. The analysis is proposed also in a non-stationary framework, in which the influence of time dependence and the inertial forces is taken into account. In order to investigate the accuracy and to validate the proposed methodology, comparisons with experimental data and numerical results are compared. Finally, the parametric study in terms of z-pins characteristics is also developed. © 2016 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of ECF21. Keywords: Moving mesh methods, ALE, Cohesive elements, Layered structures 1. Introduction Multilayered composites are frequently utilized in many structural applications. Traditional fiber composites are manufactured by stacking together a number of plies, in which the fibers are oriented to provide in-plane reinforcements for the composite. A direct consequence of this process is that no fibers are positioned across the 21st European Conference on Fracture, ECF21, 20-24 June 2016, Catania, Italy A cohesive finite element model based ALE formulation for z-pins reinforced multilayered composite beams Marco Francesco Funari, Fabrizio Greco, Paolo Lonetti* Department of Civil Engineering, University of Calabria, Via P. Bucci, Cubo39B, 87030, Rende, Cosenza, Italy. Abstract A computational formulation able to simulate fast crack growth in multilayered composite reinforced with z-pins is proposed. In particular, in order to identify the initiation and the growth of the crack, a moving mesh strategy, based on ALE appr ach, is combined with a cohesive me odology, in which weak based moving connections with th boundary adjoining layers are implem nted by using a finite lement formulation. Contrarily, z-pin re forced area was s mulated with deformation of a et of discr te onlinear springs fix d to mate ial domain. Desp te existing metho ologies available from the literature, the present paper p oposes computational procedure able to study the dynam c crack growth in composite structur s with a relatively low computational efforts. The a ysis is proposed al o in a non-st tionary frame ork, in which he influence of time dependence and the inertial ces is taken into acc unt. In order to i vestigate the curacy and to validat the prop sed methodology, com arisons wit experimental data and umerical results are compared. Finally, the parametric study in ter s of z-pins haracteristics is als d veloped. © 2016 The Authors. Published by Elsevier B.V. Peer-review under respons bility of the Scientific Committee of ECF21. Keywords: Moving mesh methods, ALE, Cohesive elements, Layered structures 1. Introduction Multilayered composites are frequently utilized in many structural applications. Traditional fiber composites are manufactur d by stack ng together a number of plies, in which the fibers are or ented to provide in-pl n rei forcem nts for h comp site. A direct consequenc of this process is that no fibers are p sitione across th Copyright © 2016 The Authors. Published by Elsevier B.V. This is an open access article u der 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. * Corresponding author. Tel.: +39-0984-496917; fax: +39-0984-496917. E-mail address: lonetti@unical.it 2452-3216 © 2016 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of ECF21. * Corresponding author. Tel.: +39-0984-496917; fax: +39-0984-496917. E-mail address: lonetti@unical.it

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.2016.06.059