PSI - Issue 2_B

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 Struc ural Integrity 2 (2016) 2591–2597 Available online at www.sciencedirect.com ScienceDirect Structural Integrity Procedia 00 (2016) 000–000 il l li t . i i t. tr t r l I t rit r i ( )

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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 Probabilistic failure analysis for glass components under general loading conditions Alberto Ramos*, Miguel Muniz-Calvente, María Jesús Lamela-Rey, Pelayo Fernández, Alfonso Fernández-Cant li. Polytechnic School of Engineering of Gijón. University of Oviedo. Campus de Viesques, 33204 Gijón, Spain. Abstract In this work, an experimental programme consisting in four-point bending and coaxial double ring tests is performed on glass specimens with different dimensions. The results are analyzed using a novel probabilistic model aiming at proving the suitability of the three-parameter Weibull distribution function to predict failure of structural glass elements under general loading cases. The tests evaluation consists in the calculation of the stress distribution for each test modality using a finite element commercial code, in the election of a reference parameter and a failure criterion and in the estimation of the shape, location and scale Weibull parameters defining the failure cumulative distribution function for the reference p rameter and the effective area. The sati factory results obtained confirm the applicability of t e procedure. © 2016 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of ECF21. Keywords: Structural Glass; Experimental Programme; Probabilistic Design. 1. Introduction Glass, as a ceramic material, is characterized by its brittleness, evidencing a fracture behavior conditioned by the presence and random distribution of microcracks or defects on the plate surface generated during the fabrication process in the float furnace. The fracture occurs as a result of the tension stress intensification at the cracks, causing l t i l f i i f ij . i it f i . i , ij , i . t i , i t l i ti i i i i l l i t t i l i it i t i i . lt l i l ili ti l i i t i t it ilit t t t i ll i t i ti ti t i t il t t l l l t l l i . t t l ti i t i t l l ti t t i t i ti t t lit i i it l t i l , i t l ti t il it i i t ti ti t , l ti l i ll t i i il l ti i t i ti ti t t t ti . ti t lt t i i t li ilit t . t . li l i . . Peer-revie onsibility of the Sci ti i o itt . : tr t r l l ; ri t l r r ; r ili ti i . . i l , i t i l, i t i it ittl , i i t i iti t i t i ti i t t l t t i t i ti i t l t . t lt t t i t i t i i ti t t , i 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. Keywords: High Pressure Turbine Blade; Creep; Finite Element Method; 3D Model; Simulation.

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* Alberto Ramos. Tel.: +34-985182051; fax: +34-985182433. E-mail address: ramosfalberto@uniovi.es - il : r f l rt i i.

* 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 r . . i i ilit t i ti i itt . - t r . 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.2016.06.324