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) 3601–36 9 Available online at www.sciencedirect.com ScienceDirect Structural Integrity Procedia 00 (2016) 000–000 il l li t . i i t. t t l t it i

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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 Fretting fatigue induced surface cracks under shrink fitted main bearings in wind turbine rotor shafts Thes Rauert a *, Jenni Herrmann a , Peter Dalhoff a , 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 This paper deals with the phenomenon of fretting fatigue on the rotor shaft of a wind turbine at the shrink fit of the main bearing. The sensitivity of the rotor shaft for growing cracks that nucleate at the bearing seat is investigated and available approaches of fretting fatigue prediction for shaft-hub and shaft-bearing connections are presented. Their application to the rotor shaft of a wind turbine is assessed and a validation on a full scale and a 1:10 scale rotor shaft fatigue test rig is proposed. © 2016 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of ECF21. Keywords: rotor shaft; wind turbine; fretting fatigue; wear; crack growth 1. Introduction The rotor shaft is a highly safety relevant component of a wind turbine, since it carries the rotor of the turbine. Along with the trend of growing rotor diameters and hub heights, the loads on the rotor shaft and the main bearing of a wind turbine are continuously increasing. According to Herrmann et al. (2015), more compact drive train designs are being developed, with shorter and hollow rotor shafts. Due to this, relative movements between the rotor shaft and the shrink fitted inner ring of the main bearing occur. These relative movements can lead to the undesirable phenomenon of fretting fatigue. The contacting surfac s are deteriorating a d the fatigue strength of the shaft is reduced unnoticed, see Fig. 1. e a a a e a b a tit t f l ffi i t t , i it f li i , li , , b tit t f t t l ics, Universit f t , Albert i tein-Str. 2, 1 t , i l it t tti ti t t t i t i t t i it t i i . iti it t t t i t t l t t t i t i i ti t il l tti ti i ti t t i ti t . i li ti t t t t i t i i li ti ll l : l t t ti t t i i . t . li l i . . i i ilit t i ti i itt . t t; i t i ; tti ti ; ; t . rotor shaft is a highly safety relevant component of a wind turbine, since it carries the rotor of the turbine. Along w , . . , , . , . . , . . 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/). Pe r-r view und r 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: thes.rauert@haw-hamburg.de i t . l.: .

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* 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. t . li l i . . i i ilit t i ti i itt .

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.2016.06.449