PSI - Issue 2_A

ScienceDirect Available online at www.sciencedirect.com Av ilable o line at ww.sciencedire t.com cienceDirect Structural Integrity Procedia 00 (2016) 000 – 000 Procedia Struc ural Integrity 2 (2016) 2951–2958 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 Fatigue and fracture mechanical behaviour of a wind turbine rotor shaft made of cast iron and forged steel Jenni Herrmann *, Thes Rauert a , Peter Dalhoff a and Manuela Sander b a Institute of Renewable Energy and Energy-efficient Systems, Hamburg University of Applied Sciences, Berliner Tor 21, 20099 Hamburg, Germany b Institute of Structural Mechanics, University of Rostock, Albert-Einstein-Str. 2, 18059 Rostock, Germany Abstract To reduce uncertainties associated with the fatigue behaviour of the highly safety relevant wind turbine rotor shaft and also to review today’s design practice the fatigue life time is tested on a full scale test rig. Further investigations of weight saving potentials contribute to suggestions for the usage of other materials. Therefore, a comprehensive comparison regarding the fatigue and the fracture mechanical behaviour of the rotor shaft made of different materials is done. For the loading situation it is distinguished between test conditions and a realistic cumulative frequency distribution of loads in a wind turbine. © 2016 The Authors. Publish d by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of ECF21. Keywords: rotor shaft; wind turbine component test; cast iron; forge steel; fa igue test rig; remaining life 1. Introduction Because of various wind and environmental conditions, wind turbines have to withstand enormous loads over a life of 20 years. Consequently, in terms of growth in wind turbine size, not just the height of the system and the rotor diam ter increase, all drive train compon s have to be scaled up regarding the new conditions. For economic reasons it should be figured out, if there are possibilities for optimization with respect to component weight. If the weight of a drive train component decreases, the material usage of the structure below could also be reduced and hence the costs. t a e er a nde b To reduce uncertainties associated with the fatigue behaviour of the highly safety rele 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.: +49-40-42875-8661. E-mail address: jenni.herrmann@haw-hamburg.de

* 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 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.2016.06.369