PSI - Issue 2_B

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 2 (2016) 05 – 57 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 Memory effects i variable amplitude and m ltiaxial fatigue crack growth: an incremental approach S. Pommier* LMT (ENS Cachan, CNRS, Université Paris Saclay), 61, avenue du Président Wilson, 94235 Cachan, France Abstract This paper presents an incremental approach for modelling fatigue crack growth with memory effects due to the non-linear behavior of the material. This approach is developed at LMT since 2003, in collaboration with several industrial partners, mainly with Snecma, SAFRAN Group, EDF and AREVA and SNCF. The first part of this paper presents the context and the objectives, and the key assumptions on which the model is based. The second part presents some examples of applications of the model, fatigue crack growth in mode I conditions, under variable amplitude loading; non-isothermal situations; crack growth in coupled environmental and fatigue loading conditions; extension of the model to non-proportional mixed mode loading conditions, and to short cracks. The last part presents some ongoing work, possible developments and scientific challenges that remain to be overcome. © 2016 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of ECF21. Keywords: fatigue ; crack growth ; memory effects ; mixed mode. 1. Introduction Accurate predictions of fatigue crack propagation and of the service life of critical components in operating conditions, remains difficult, for the following reasons:  2D / 3D : Stress concentration area where short cracks may be initiated usually display spatial gradient and a certain degree of multiaxiality over a domain which sizes is in the order of magnitude with the short crack to long crack transition length. However, data and crack propagation models are often based on mode I long crack growth behavior. 21st European Conference on Fracture, ECF21, 20-24 June 2016, Catania, Italy Memory effects in variable amplitude and multiaxial fatigue crack growth: an incremental approach S. Pommier* LMT (ENS Cachan, CNRS, Université Paris Saclay), 61, avenue du Président Wilson, 94235 Cachan, France Abstract This paper presents an incremental approach for modelling fatigue crack growth with memory effects due to the non-linear behavior of th material. This approach is devel ped at LMT since 2003, in collaboration with several industrial partners, mainly with Snecma, SAFRAN Group, EDF and AREVA and SNCF. Th first part of this paper presents the context and the objectives, and the key assumptions on which the model is b sed. The second part presents som examples of applications of the mod l fatigue crack growth in m de I conditions, under v riable amplitude loading; non-i th rm l situati ns; cra k growth in coupl d environmental and fatigue loading conditions; extens on of the mo l to non-pr portional mixed mode loading c nditio s, and to short cr cks. The l st part presents some ongoing work, possibl developments and scientific challenges that remain to be ove come. © 2016 The Authors. Published by Elsevier B.V. Peer-review under espons bility of the Scientific Committee of ECF21. Keywords: fatigue ; crack growth ; memory effects ; mixed mode. 1. Introduction Accurate predictions of fatigue cra k propagation and of the rvice life of critical components in operating conditions, mains difficult, for the following reasons:  2D / 3D : Stress concentration area where short cracks may be initiated usually display spatial gradient and a certain degr e of multiaxiality over a domain whi h sizes is in the order of magnitude wi h the shor crack to long crack transition length. However, d ta and rack propagation models are of en based on mode I long crack rowth behav r. 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.

* 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 ECF21. * Corresponding author. Tel.: +33-1-69337704; fax: +33-1-47402240. E-mail address: sylvie.pommier@universite-paris-saclay.fr * Corresponding author. Tel.: +33-1-69337704; fax: +33-1-47402240. E-mail address: sylvie.pommier@universite-paris-saclay.fr

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.2016.06.007