PSI - Issue 3

ScienceDirect Available online at www.sciencedirect.com Av ilable o line at ww.sciencedire t.com ScienceDirect Structural Integrity Procedia 00 (2016) 000 – 000 Procedia Structu al Integrity 3 (2017) 144–152 Available online at www.sciencedirect.com ScienceDirect Structural Integrity Procedia 00 (2017) 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. Copyright © 2017 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 IGF Ex-Co. XXIV Italian Group of Fracture Conference, 1-3 March 2017, Urbino, Italy On the fracture behavior of polyurethane notched components F. Berto a,* , L. Marsavina b , S.M.J. Razavi a , M.R. Ayatollahi c a Department of Mechanical and I dustri l Engineering, Norwe ian University of Science and Technology (NTNU), Richard Birkelands vei 2b, 7491, Trondheim, Norway. b Department of Mechanics and St ength of Materials, Univeritatea Politehnica Timisoara, Timisoara, Romania. c Department of Mechanical Engineering, Iran University of Science and Technology, Narmak, 16846, Tehran, Iran. Abstract Local Strain Energy Density represents an engineering approach for assessing the brittle fracture of cracked and notched components. Experimental determination of fracture parameters (critical value of deformation energy W c in a local finite volume around the notch tip and the radius of the control volume R c ) represents a key issue. The paper presents a methodology to determine these parameters using a notched tensile specimen. The obtained values will be used to predict the fracture load in different types of notches and cracked specimens under mode I; for cracked specimens under mixed mode and mode II has defined a personal approach that confirms PUR foams can be treated as brittle materials. The considered specimens are made of poly rethane materials f different densities from 100 to 651 kg/m 3 . © 2017 The Authors. Published by Elsevier B.V. Peer-review under responsibility of th Scientific Committee of IGF Ex-Co. Keywords: SED, PUR foams, static failure, fracture parameters. 1. Introduction Polyurethane (PUR) materials represent a class of organic units joined by urethane links. They can be manufactured in a wide range of densities: e i g i n Bi , v o a t p u m s r t den o 651 /m 3 . 2 A h r . b E v . -r i r spo l ty h nt t of GF x C w ds , s a a c e od ct u a R er s r a u c de i i © 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.: +47-735-93831. E-mail address: filippo.berto@ntnu.no

* Corresponding author. Tel.: +351 218419991. E-mail address: amd@tecnico.ulisboa.pt 2452-3216 © 2017 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of IGF Ex-Co. 5 r v r nsib y

2452-3216 © 2016 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of PCF 2016. Copyright © 2017 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 IGF Ex-Co. 10.1016/j.prostr.2017.04.025