PSI - Issue 2_B

ScienceDirect Available online at www.sciencedirect.com Av ilable o line at ww.sciencedire t.com ienceDirect Structural Integrity Procedia 00 (2016) 000 – 000 Procedia Structu al Integrity 2 (2016) 253–26 Available online at www.sciencedirect.com ScienceDirect Structural Integrity Procedia 00 (2016) 000–000 c

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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. 21 st European Conference on Fracture, ECF21, 20-24 June 2016, Catania, Italy Time dependent fracture behaviour of a carbon fibre composite based on a (rubber toughened) acrylic polymer Tommaso Pini a, *, Francesco Briatico-Vangosa a , Roberto Frassine a , Marta Rink a a Dipartimento di Chimica, Materiali e Ing. Chimica “Giulio Natta”, Politecnico di Milano, Piazza Leonardo da Vinci 32, Milano – 20133, Italy The fracture behaviour of continuous carbon fibre laminates based on plain and rubber-toughened acrylic resins was investigated focusing on the influence of rate and temperature. The tensile behaviour of the two matrices was also characterized for subsequent analysis. In all cases the experimental window was extended by applying the time-temperature equivalence postulate. Fracture toughness at varying crack propagation rate turned out to have opposite trends for the two matrices. For the plain acrylic resin, a monotoni ally increasing trend with crack rate was found in agreement with viscoelastic fracture theories. For the rubber-toughened resin the change of the failure mechanisms occurring at the crack tip, resulted in a monotonically decreasing trend for increasing crack rate. Rate and temperature effects were a alysed in terms of volumetri strain during tensile t sts. Comp sites turned out t be more resistant to crack propagation than the relevant matrices in both cases. D laminatio fracture toughness turned out to have the same dependence on crack rate for rubber toughened matrix only. For composites based on the plain resin, no effect of crack rate on delamination fracture toughness was observed. © 2016 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of ECF21. Keywords: thermoplastic composites; viscoelastic fracture; volume strain; rubber toughening; yield mechanisms; 21 i a, a a a R a The fr © 2016 The Authors. Published by Elsevier B.V. w Keyword bber toughening; yield mechanisms; Copyright © 2016 The Authors. Published by Elsevi r B.V. This is an open access article under the CC BY-NC-ND license (http://cr ativecommons.org/licenses/by-nc-nd/4.0/). Peer-review under responsibility of the Scientific Committee of ECF21. Abstract

© 2016 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of PCF 2016. 1. Introduction

Keywords: High Pressure Turbine Blade; Creep; Finite Element Method; 3D Model; Simulation. Composite materials a e nowadays widely us d in structural applications for which weight reduction is a critical issue. The interlaminar fracture toughness of a composite material is a fundamental property to investigate when

* Corresponding author. Tel.: +39-2-23994711; fax: +39-2-7063-8173. E-mail address: tommaso.pini@polimi.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.

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.2016.06.033