PSI - Issue 5

ScienceDirect Available online at www.sciencedirect.com Av ilable o line at ww.sciencedire t.com Sci ceDirect Structural Integrity Procedia 00 (2016) 000 – 000 Procedia Structu al Integrity 5 (2017) 896–903 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. 2nd International Conference on Structural Integrity, ICSI 2017, 4-7 September 2017, Funchal, Madeira, Portugal Mix d mode I/II/III fatigue crack growth in S355 steel D. Rozumek a *, Z. Marciniak a , G. Lesiuk b , J.A.F.O. Correia c a Department of Mechanics and Machine Design, Opole University of Technology, Mikolajczyka 5, 45-271 Opole, Poland b Faculty of Mechanical Engineering, Department of Mechanics, Material Science and Engineering, Wrocł aw University of Science and Technology, Smoluchowskiego 25, 50- 370 Wrocław, Poland c INEGI/Faculty of Engineering, University of Porto, Rua Dr. Roberto Frias, 4200-465 Porto, Portugal The paper presents the results of an experimental investigation of the crack path and description of fatigue crack growth in plane specimens made of S355 steel under tension and bending with torsion. Specimens with rectangular cross-sections and stress concentrator in the form of external one-sided sharp notch were used. The tests were performed under the load ratios R = 0, 0.1. The tests were performed under the different slot inclinations (mode I+II) and different ratios of torsion to bending moments (mode I+III). The results of the experimental tests have been de scribed using ΔK stress intensity factor range. © 2017 The Authors. Publishe by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of ICSI 2017. Keywords: fatigue crack growth; stress ratio; tension; bending with torsion; notch 1. Introduction Elements of machines and structures wo king under variable loading are often subjected to multiaxial loading. Materials that are used for the manufacture of those structural components contain defects and flaws, which effect on durability. Theref re, it is v ry important to be able to predict the initiation and the evolution of fatigue crack as a function of loading (Pyrzanowski, 2007). In the literature can be found various problems concerning of fatigue crack growth for simple load conditions (modes I, II, III) given in references by Beretta et al. (2011) or Rozumek and Marciniak (2012), as well as for mixed modes loading to which can by qualify among others: tension with torsion, a b C c ole, Poland concentrator in the form of external one-sided sharp notch were used. The tests were performed under the load ratios R = 0, 0.1. r Marciniak (2 12), as well as for mixed © 2017 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of ICSI 2017 © 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. Abstract

* Corresponding author. Tel.: +48 774498410; fax: +48 77449 99 06. E-mail address: d.rozumek@po.opole.pl

2452-3216 © 2016 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of PCF 2016. 2452-3216  2017 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of ICSI 2017 10.1016/j.prostr.2017.07.125 * 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 ICSI 2017.