PSI - Issue 13

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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 Structural Integrity 13 (2018) 1762–1767 Available online at www.sciencedirect.com ScienceDirect Structural Integrity Procedia 00 (2018) 000–000 ScienceDirect Structural Integrity 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 Behaviour of Additively Manufactured Inconel 718 P oduced by Selective Laser Melting. K. Solberg a *, J. Torgersen a , F. Berto a a Norwegian University of Science and Technology, Richard Birkelandsvei 2b, 7034 Trondheim, Norway Abstract Selective Laser Melted (SLM) Inconel 718 has promising use in various applications, where complex design and excellent strength is required. Yet fatigue properties of respective components in critic l load bearing applications are yet poorly understood. Here, we investigate the fatigue behaviour of differe t notch geometries of as-build specimens at room temperature. The fatigue strength of semi-circular and v-shaped notch geometries are evaluated and the results compared with those of smooth specimens. The stress fields of the different geometries are analysed by use of analytical models and numerically by use of finite element. The fatigue data shows a smaller scatter in the geometries with printed overhangs than the ones without. High values of notch sensitivity is obtained for both notch geometries. Fatigue properties of AM Inconel 718 are so far underexplored, this research therefore adds to the applicability of this material and manufacturing method for load bearing applications. © 2018 The Aut ors. Published by Elsevier B.V. Peer-review under responsibility of the ECF22 organizers. Keywords: Fatigue, Additive Manufacturing, Inconel 718, Not h, El stic St ess Fi l s 1. Introduction Inconel 718 is a Ni-based superalloy with high strength, corrosion and creep resistance at high temperatures. However, igh strength and hardness makes it difficult to process the material with conventional machining and fabrication methods. AM s a new manufacturing ethod that allows building components in a layer-by-layer method assisted by 3D models created in computer aided software, allowing complex geometries and internal structures not possible through machining or other manufacturing methods. ECF22 - Loading and Environmental effects on Structural Integrity Fatigue Behaviour of Additively Manufactured Inconel 718 Produced by Selective Laser Melting. K. Solberg a *, J. Torgersen a , F. Berto a a Norwegian University of Science and Technology, Richard Birkelandsvei 2b, 7034 Trondheim, Norway Abstract Selective Laser Melted (SLM) Inconel 718 has promising use in various applications, where complex design and excellent strength is required. Yet fatigue properties of respective components in critical load bearing applications are yet poorly understood. Here, we investigat th fatigue behaviour of differe t no ch geometries of as-build specimen at ro temperature. The fatigue stren t of s mi-circular and v-shaped notch geom tries are evaluated and the results compared with those of smooth specim n . The stress fi lds of the diff rent eometries a e analysed by use of analytical models and nu rically by use of finit element. The fati ue data shows a smaller scatter i the e etries with printed overhangs than the ones without. High values of notch sensitivity i obtained for both notch geometries. F tigue properties AM In onel 718 are so far underexplored, this res arch therefor adds to the applicability of thi material and manufacturing metho f r load bearing applications. © 2018 The Authors. Published by Elsevier B.V. Peer-review under resp sibility of the ECF22 organizers. K ywords: Fatigue, Additive Manufacturing, Inconel 718, Notch, Elastic Str ss Fields 1. Introduction Inconel 718 is a Ni-based superalloy with high strength, corrosion and creep resistance at high temperatures. However, high strengt and hardness makes it difficult to proce s the materi l with conventional machining and fabrication methods. AM is a new manufacturing method that allows building components in a layer-by-layer method assisted by 3D models creat in computer aided software, allowing complex geometries and internal structures not possible through machining or other manufacturing methods. © 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 © 2018 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the ECF22 organizers. 2452-3216 © 2018 The Autho s. Published by Elsevier B.V. Peer-review under responsibility of the ECF22 organizers. * Corresponding author. Tel.: +47 975 00 723. E-mail address: klas.solberg@ntnu.no * Corresponding author. Tel.: +47 975 00 723. E-mail address: klas.solberg@ntnu.no

2452-3216  2018 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the ECF22 organizers. 10.1016/j.prostr.2018.12.371

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