PSI - Issue 5

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 Structu al Integrity 5 (2017) 393–40 Available online at www.sciencedirect.com ScienceDirect Structural Integrity Procedia 00 (2017) 000 – 000 il l li t . i i t. tr t r l I t rit r i ( )

www.elsevier.com/locate/procedia . l i r. /l t / r 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. 2nd International Conference on Structural Integrity, ICSI 2017, 4-7 September 2017, Funchal, Madeira, Portugal Fatigue Behaviour Evaluation of Additively and Conventionally Produced Materials by Acoustic Emission Method Vendula Kratochvilov 1 , Fr ntisek Vlasic 1 , Pavel Mazal 1 , David Palousek 1 * 1 Brno University of Technology, Technicka 2896/2, 616 69 Brno, Czech Republic Additive manufacturing of metals is today one of the most growing fields in materials research. Selective laser melting (SLM) allows to produce metal parts with complicated shapes, but the quality of produce material is relati ely low (in compare with conventionally produced materials). The main aims of latest studies is to improve materials properties and reach the same or better quality. Presented paper shows the comparison of fatigue behaviour of SLM and conventional material using copper (Cu7.2Ni1.8Si1Cr) and aluminium (AlCu2Mg1.5Ni and AlSi10Mg) alloys. SLM and standard material samples were subjected to bending fatigue tests which were supplemented by acoustic emission (AE) measurement and fractography analysis. The results from AE measurement allows to analyse fatigue process, determine different fatigue stages and compare the results from SLM and standard material in more detail. The results show that the main difference between fatigue behaviour of SLM and standard material is not only in total fatigue life (the SLM material has significantly worse fatigue resistance), but mainly in the length of fatigue stages and in mechanism of crack development. As we expected, the fatigue resistance of SLM is strongly affected by amount of production defects. © 2017 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of ICSI 2017. Keywords: Selective laser meltin ; additive manufacturing; acoustic emission; fatigue Portugal a si 1 1 1 1 i it f l y, Technicka 2896/2, 616 69 Brno, Czech Republic iti t i t l i t t t i i l i t i l . l ti l lti ll t t l t it li t , t t lit t i l i l ti l l i it ti ll t i l . i i l t t t i i t i t i l ti t tt lit . t t i ti i ti l t i l i . i . i l i i l . i l i ll . t t i l l j t t i ti t t i l t ti i i t t l i . lt t ll t l ti , t i i t ti t t lt t t i l i t il. lt t t t i i t ti i t t i l i t only in total fatigue life (the SLM material has significantly wo ti i t , t i l i t l t ti t i i development. As we expected, the fatigue resistance of SLM is strongly affected by amount of production defects. © 17 The Authors. Publi ed by El i r . . i i ilit t i ti i itt . : l ti l r lti g; iti f t ri ; ti i i ; f ti © 2017 The Authors. Published by Elsevier B.V. Peer-review under responsibility f the Scientific Committee of ICSI 2017 Abstract

© 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.: +420-54114-3240. E-mail address: xkrato04@vutbr.cz i t r. l.: - - . - il : r t t r. rr

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.2017.07.187 * 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. l i r . . i i ilit t i ti i itt . - t r . li