PSI - Issue 2_A

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 Struc ural Integrity 2 (2016) 3697–37 4 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 Crack surface morphology and grain misorientation in fatigued aluminium alloy AA7050 samples after interrupted ageing and retrogression-reageing treatments André L. M. Carvalho a *, Juliana P. Martins b , Enrico Salvati c , Tan Sui c , Alexander M. Korsunsky c a Department of Material Engineering, State University of Ponta Grossa, 4748 General Carlos Cavalcanti Ave, Ponta Grossa 84030-900, Brazil b Department of Chemical Engineering, Federal University of Technology – Paraná, Monteiro Lobato Ave, Ponta Grossa 84016-210, Brazil c Multi-Beam Laboratory for Engineering Microscopy (MBLEM), Department of Engineering Science, University of Oxford, Parks Road, Oxford OX1 3PJ, United Kingdom Abstract We present the investigation of fatigue crack surface morphology and crystallographic grain orientation in samples of aluminium alloy AA7050 that had been subjected to interrupted ageing (T6I4-65) and retrogression-reageing (RRA) heat treatments. Both T6I4-65 and RRA ageing treatments generate bimodal (particle size) microstructural features. A single tensile overload was applied and its influence on the crystallographic grain orientation was evaluated using electron backscatter diffraction (EBSD). The results reveal that T6I4-65 and RRA heat treatments c ntribute to the increased occu rence of planar slip features in t e form of small and larg flat facets, r spectively. T6I4-65 condition leads to a g eat r degree of lattice misorientation in the vicinity of fa igu crack tip than the RRA condition wh ch is likely to be t evidence of increased plastic deformation due to the ov rload. © 2016 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of ECF21. 21st European Conference on Fracture, ECF21, 20-24 June 2016, Catania, Italy Crack surface morphology and grain misorientation in fatigued aluminium alloy AA7050 samples after interrupted ageing and retrogression-reageing treatments André L. M. Carvalho a *, Juliana P. Martins b , Enrico Salvati c , Tan Sui c , Alexander M. Korsunsky c a Department of Material Engineering, State University of Ponta Grossa, 4748 General Carlos Cavalcanti Ave, Ponta Grossa 84030-900, Brazil b Department of Chemical E gineering, Federal University of Technology – Paraná, Monteiro Lobato Ave, Ponta Grossa 84016-210, Brazil c Multi-Bea Laboratory for nginee ng Microscopy (MBLEM), Department of E gineering Science, University of Oxford, Parks Road, Oxford OX1 3PJ, United Kingdom Abstract We present the investigation of fatigue crack surface morphology and crystallographic grain orientation in samples of aluminium alloy AA7050 that h d be n subjected to interrupted ageing (T6I4-65) and retrogression-reageing (RRA) heat treat ents. Both T6I4-65 and RRA ageing treatments generat bimodal (particle size) microstructural features. A single tensile overload was applied and its influ nce on th crystallographic grain orientation was evaluated using electron backscatter diffraction (EBSD). The res lts reveal that T6I4-65 and RRA heat treatments contribut to the increased o currence of planar slip features in he form of small and large lat fa ets, respectivel . T6I4-65 ondition leads to a great r d gree f l ttice misorientation in the vicinity of fatigu crack ip than the RRA condi ion which is likely to be the videnc increased plastic deform tion due to the overload. © 2016 Th Authors. Published by El vier B.V. Peer-review under responsibility of the Scientific Committee of ECF21. Keywords: Fatigue fracture surface; EBSD; Misorientation; T6I4-65 and RRA conditions. 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: Fatigue fracture surface; EBSD; Misorientation; T6I4-65 and RRA conditions.

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 un r responsibility of the Scientific Committee of ECF21. 2452-3216 © 2016 The Authors. Published by Elsevier B.V. Peer review under r sponsibility of the Scientific Committee of ECF21. * Corresponding author. Tel.: +55- 42-3220-3340; fax: +55- 42-3220-3072. E-mail address: andrelmc@uepg.br * Corresponding author. Tel.: +55- 42-3220-3340; fax: +55- 42-3220-3072. E-mail ad ress: andrelmc@uepg.br

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.2016.06.459