PSI - Issue 7

ScienceDirect Available online at www.sciencedirect.com Av ilable o line at ww.sciencedire t.com cienceDirect Structural Integrity Procedia 00 (2016) 000 – 000 P o edi Structural Integr ty 7 (2017) 75–83 Available online at www.sciencedirect.com Sc enceD r ct Structural Integrity Procedia 00 (2017) 000–000 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. 3rd International Symposium on Fatigue Design and Material Defects, FDMD 2017, 19-22 September 2017, Lecco, Italy Influence of defect size on the fatigue resistance of AlSi10Mg alloy laborated by selective laser melting (SLM) Julius N. Domfang Ngnekou a,b *, Yves Nadot a , Gilbert Henaff a , Julien Nicolai a , Lionel Ridosz b a Institut Pprime UPR CNRS 3346, Department of Physique and Mechanics of Materials, ENSMA-Université de Poitiers, 1 avenue Clément Ader, Téléport 2, 86960 Chasseneuil-Futuroscope, France. b Zod ac Aerospace, 61 r e Pierre Curie, 78370 Plaisir, France Abstract In the aircraft industry, Additive Manufacturing (AM) process is receiving more and more attention to produce parts with complex geometry and also leads to important weight reduction. Due to complex microstructure and the presence of defect both inherited from this specific process, it is necessary to assess the fatigue resistance of the material constitutive of manufactured parts prior to certification. This work is precisely tackling this issue with a special attention aid to the role of microstructural p rameters and defects on fatigue life. With this aim, samples were built by a powder-bed process called SLM. Specimens were built with two configurations (0° a d 90°) in order o evaluate the impact of the induced anisotropy of microstructure on fatigue prop rties. X-Ray 3D tomography was us d to characterize defect population by their size. Microstructure is furthermore characterized by considering four characteristic scales [1, 7, 12], melt-pools, crystallographic grains, dendritic structure and the precipitates. The fatigue properties are determined by establishing S-N curves for as-built and heat-treated samples for R= -1. The defect size responsible for the fatigue damage initiation is determined in each sample so as to establish a relation between the fatigue limit and the defect size by means of Kitagawa type diagrams. It is shown that the defect size is the first order parameter in terms of the fatigue resistance. Through the Kitagawa diagrams for as-built and heat treated samples, we quantify the improvement of the fatigue resistance due to the peak hardening treatment. 3rd International Symposium on Fatigue Design and Material Defects, FDMD 2017, 19-22 September 2017, Lecco, Italy Influence of de ect size on the fatigue resistance of AlSi10Mg all y elaborated by selective laser melting (SLM) Julius N. Domfang Ngnekou a,b *, Yves Nadot a , Gilbert Henaff a , Julien Nicolai a , Lionel Ridosz b a Institut Pprime UPR CNRS 3346, Department of Physique and Mechanics of Materials, ENSMA-Université de Poitiers, 1 avenue Clément Ader, Téléport 2, 86960 Chasseneuil-Futuroscope, France. b Zodiac Aerospace, 61 rue Pierre Curie, 78370 Plaisir, France Abstract In the aircraft industry, Additive Manufacturing (AM) process is receiving more and more attention to produce parts wi complex geometry an also leads to important weight r duction. Due to c mplex ic os ruc ure and the pr sence of defect both inherited from this specific process, it is n cessary to assess the fatigue resistance of mat rial constitutive of manufactu ed parts rior to certification. This work is pr cisely t ckling th issue with a sp c l atten ion paid to the role of micro tructural parameters and defects on fatigue life. With this a m, amples were built by a p wder-bed process called SLM. Specimens w re built with w configurations (0° and 90°) in order to valuate the impact of the in uced nisotropy of m crostructure on fatigue prop r ies. X-Ray 3D tomography was used to c aracterize d f ct population by their s ze. Mi ro tructure is furt rmore charac erized by considering four stic scales [1, 7, 12], melt-pools, crystallog aphic grains, dend itic st ucture nd the precipitate . The fatig e proper ies are determined by establishing S-N curves for as-built and heat-treated samples for R= -1. The defec siz responsible for th fatigue dam ge in tiation is det rmined in each sample so as to establish a relation betw en th fatigue limit and the defect size by means of Kitagawa type diagrams. It is shown hat the defect size is the first rder parameter in terms of the fatigue resistance. Through the Kitagawa diagrams for as-built and heat trea ed samples, we quan ify the i pr vement of the fatigue resistance due to the peak hardening tre tment. © 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. Copyright © 2017 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of the 3rd International Symposium on Fatigue Design and Material Defects. © 2017 The Authors. Published by Elsevier B.V.

© 2017 The Authors. Published by Elsevier B.V.

* Corresponding author. E-mail address: julius.domfang@ensma.fr * Corresponding author. E-mail address: julius.domfang@ensma.fr

* 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 the 3rd International Symposium on Fatigue Design and Material Defects. 2452-3216 © 2017 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of the 3rd International Symposium on Fatigue Design and Material Defects.

2452-3216 © 2016 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of PCF 2016.

2452-3216 Copyright  2017 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of the 3rd International Symposium on Fatigue Design and Material Defects. 10.1016/j.prostr.2017.11.063