PSI - Issue 13

ScienceDirect Available online at www.sciencedirect.com Av ilable o line at www.sciencedire t.com ScienceDirect Structural Integrity Procedia 00 (2016) 000 – 000 Procedia Structural Integrity 13 8 74–78 Available online at www.sciencedirect.com ScienceDirect Structural Integrity Procedia 00 (2018) 000 – 000 Available online at www.sciencedirect.com ScienceDirect Structural I tegrity Procedia 00 (2018) 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. © 2018 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the ECF22 organizers. ECF22 - Loading and Environmental effects on Structural Integrity Fatigue strength of notched specimens made of Ti-6Al-4V produced by Selected Laser Melting technique S.M.J. Razavi*, F. Berto Department of Mechanical and Industrial Engineering, Norwegian University of Science and Technology (NTNU), Trondheim 7491, Norway Abstract As an Additive Manufacturing (AM) method, Selective Laser Melting (SLM) allows fabrication of metallic components of any desired geometry with densities greater than 99.5%. This method is usually used for geometrically optimized components with complex geometries including various kinds of notches. Hence, it is important to have a clear information about the fatigue behavior of notched components made by SLM method. This paper evaluates the fatigue behavior of Ti-6Al-4V blunt V-notched and circular notched samples produced by SLM. The fatigue results were then compared with those of the corresponding smooth samples. The fracture surfaces of the tested samples were evaluated using Environmental Scanning Electron Microscopy (ESEM) and the crack initiation points and fracture mechanisms were identified. © 2018 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the ECF22 organizers. Keywords: Fatigue; Notch Mechanics; Selective Laser Melting (SLM); Semi-circular notch, V notch. 1. Introduction In the ambit of continuous digitalization of manufacturing processes, modern short product life cycles and the ever growing ne d for high performanc , low weight products with minimal production needs, we face stringent requirements o both time and s phistication of modern structural design and property prediction. In order to digitally produce the advanced components of the future designs, conventional design techniques, structural assessment methods and production routines fail to achieve necessary requirements for structural complexities which enhance the ECF22 - Loading and Environmental effects on Structural Integrity Fatigue strength of notched specimens made of Ti-6Al-4V produced by Selected Laser Melting t chnique S.M.J. Razavi*, F. Berto Department of Mechanical and Industrial Engineering, Norwegian University of Science and Technology (NTNU), Trondheim 7491, Norway Abstract As an Additive Manufacturing (AM) method, Selective Laser Melting (SLM) allows fabrication of metallic components of any desired geometry with densities greater than 99.5%. This method is usually used for geometrically optimized components with complex geometries including va ious kinds of notches. H nce, it is important to have a clear information about th fatigue behavior of notched components made by SLM method. This paper evaluates the fatigue behavior of Ti-6Al-4V l nt V-notched and circular n tc e sa les produced . The fatigue results were then compared with th se of the corresponding smooth samples. The fracture surfaces of the tested samples were evaluated using Environ ental Scanning Electron Microscopy (ESEM) and th crack initiation points and fractur mechanisms were identified. © 2018 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the ECF22 organizers. Keywords: Fatigue; Notch Mechanics; Selective Laser Melting (SLM); Semi-circular notch, V notch. 1. Introduction In the ambit of continuous digitalization of manufacturing processes, modern short product life cycles and the ever growing need for high performance, low weight products with minimal production needs, we face stringent requirements on both time and sophistication of modern structural design and property prediction. In order to digitally produce the advanced components of the future designs, conventional design techniques, structural assessment methods and production routines fail to achieve necessary requirements for structural complexities which enhance the © 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.: +47-735-93761. E-mail address: javad.razavi@ntnu.no * Corresponding author. Tel.: +47-735-93761. E-mail ad ress: javad razavi@ntnu.no

* Corresponding author. Tel.: +351 218419991. E-mail address: amd@tecnico.ulisboa.pt 2452-3216 © 2018 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the ECF22 organizers. 2452-3216 © 2018 The Authors. Published by Elsevier B.V. Peer review under r sponsibility of the ECF22 o ganizers.

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

2452-3216  2018 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the ECF22 organizers. 10.1016/j.prostr.2018.12.013