PSI - Issue 1

ScienceDirect Procedia Structural Integrity 1 (2016) 110–117 Available online at www.sciencedirect.com Av ilable o line at ww.sciencedire t.com Scie ceDirect Structural Integ ity Procedia 00 (2016) 00 – 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. XV Portuguese Conference on Fracture, PCF 2016, 10-12 February 2016, Paço de Arcos, Portugal Proposal of a fatigue crack propagation model taking into account crack closure effects using a modified CCS crack growth model S. Blasón a , J.A.F.O. Correia b, *, N. Apetre c , A. Arcari c , A.M.P. De Jesus b , P. Moreira b , A. F rnández-Canteli a a Department of Construction and Manufacturing Engineering, University of Oviedo, Campus de Viesques, 33203 Gijón, Spain b INEGI, Engineering Faculty, U iversity of Porto, Ru Dr. Roberto Frias, 4200-465 Porto, Portugal c Technical Data Analysis, Inc., 3190 Fairview Park Drive, Suite 650, Falls Church, VA 22042, USA Abstract This paper proposes a modification of the fatigue crack growth model proposed by Castillo-Canteli-Siegele (CCS) to take into account crack opening and closure effects as well as the influence of the stress R -ratio. The theoretical model to obtain the effective stress intensity range, ΔK eff , which takes into account the effects of the mean stress and the crack closure and opening effects proposed by Correia et al . was taken in consideration in this new proposal. This last model is based on the same initial assumptions of the analytical models proposed by Hudak et al. and Ellyin . This modified CCS crack propagation model is a new version of an explicit fatigue crack propagation model, supported by mathematical and physical assumptions. © 2016 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of PCF 2016. Keywords: Fatigue; Crack Growth; Effective Stress Intensity; Crack Closure; Gumbel Distribution. 1. Introduction A reliable design of structural details taking into account fatigue damage requires a thorough knowledge of the materials behavior being used. The Fracture Mechanics based fatigue approaches are very common to assess the fatigue behavior/strength of structural details, however adequate/accurate fatigue crack propagation laws are required. Many fatigue crack propagation laws have been proposed in the literature, since the pioneer proposal by Copyright © 2015 Th Authors. Publish d by Elsevi r B.V. This is a open acc ss article under the CC BY-NC-ND license (ht p://creativecommons.o g/licenses/by-nc-nd/4.0/). Peer-review under sponsibility of the Sci ntific Committ e of PCF 2016. © 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.: +351225082151; fax: +351225081584. E-mail address: jacorreia@inegi.up.pt

* 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 PCF 2016.

2452-3216 © 2016 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of PCF 2016. Copyright © 2015 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 PCF 2016. 10.1016/j.prostr.2016.02.016