PSI - Issue 13

ScienceDirect Available online at www.sciencedirect.com Av ilable o line at www.sciencedire t.com ScienceDirect Structural Integrity Procedia 00 (2016) 000 – 000 Procedia Structural Integrity 13 (2018) 10 –1 5 Available online at www.sciencedirect.com ScienceDirect Structural Integrity Procedia 00 (2018) 000 – 000 Available online at www.sciencedirect.com 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. ECF22 - Loading and Environmental effects on Structural Integrity A study of fatigue notch sensibility on titanium alloy TiAl6V4 parts manufactured by selective laser melting L.P. Borrego a,b *, J.A.M. Ferreira b , J.D.M. Costa b , C. Capela b , J. de Jesus b a Coimbra Polytechnic - ISEC, Rua Pedro Nunes, 3030-199 Coimbra, Portugal b CEMMPRE, Department of Mechanical Enginnering, University of Coimbra, Rua Luís Reis Santos, 3030-788, Coimbra, Portugal Titanium Ti6Al4V alloy is a light alloy characterized by having excellent mechanical properties and corrosion resistance combined with low specific weight, commonly used in biomedical applications, automotive and aerospace components. Current work analyses the fatigue behavior of titanium alloy TiAl6V4 parts, manufactured by selective laser melting (SLM), intending to characterize fatigue strength from low to high life range, under constant amplitude strain control. Fatigue tests were carried out at room temperature, using round dog bone specimens where laser powder deposition occurred in layers perpendicular to the sample xle. All specimens were subjected to stress release treatment. A second batch of specimens was tested in order to investigate the notch sensibility of the material. All tests were performed under displacement control. The material was characterized n terms of the tensile me hanical properties, cycle curve, Basquin and Coffin equations. The analysis of the results show d strain-softening behavior that increase with applie strain, and non-linear respons in and plas ic r gime. In a dition, this alloy exhibited a low transition life, about 250 reversals, which can be attributed to the c mbinati n of high strength an relatively low ductility. The material revealed a notch sensibility fact , that was quantified for the round notch with a stress concentration factor K t =1.7 (with respect to the effective cross section) , increasing with fatigue life, from one for low cycle fatigue tending to 1.42 for high cycle fatigue (N f of about one million cycles). SEM analysis showed that fatigue crack initiated from the surface and propagated through the cross section, occurring in many cases multi-nucleation. © 2018 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the ECF22 organizers. © 2018 Th Authors. Published by Elsevier B.V. Peer-review und r responsibility f the ECF22 organizers. ECF22 - Loading and Environmental effects on Structural Integrity A study of fatigue notch sensibility on titanium alloy TiAl6V4 parts manufactured by selective lase melting L.P. Borrego a,b *, J.A.M. Ferreira b , J.D.M. Costa b , C. Capela b , J. de Jesus b a Coimbra Polytechnic - ISEC, Rua Pedro Nunes, 3030-199 Coimbra, Portugal b CEMMPRE, Department of Mech nic l Enginneri g, University f Coimbra, Rua Luís Reis Sant s, 3030-788, Coimbra, Portugal Abstract Titanium Ti6Al4V alloy is a light alloy characterized by having excellent mechanical properties and corrosion resistance combined with low specific weight, commonly used in biomedical applications, automotive and aerospace c mponents. Current work analyses the fatigue behavior of titanium alloy TiAl6V4 parts, manufactured by selective laser melting (SLM), intending to characterize fatigue strength from low to high life range, under constant amplitude strain control. Fatigue tests were carrie out at room mp r ture, using round d g b ne specime s wher laser powder deposition occu red in layers perp ndicular t he sample axl . All specimens were su jected to str s rel ase treatment. A s c nd batch of specimens was tested in order to investig te the notch sensibility of th material. All test were p rformed u er displacem nt control. The material was characterized in terms of the tensile mechanical properties, cycle curv , Basquin a Coffin equations. The analysis of he result s owed a stra -soften ng behavior that incre sed with a pli d tr in, and non-linear response in and plastic regime. In addit on, t is alloy exhibited a low transition life, about 250 reversals, which can be attributed to th c mbination of high str ngth and relativel low ductility. The material r vealed a notc sensibility factor, t at was quantified for the rou d notch with a stress concentration factor K t =1.7 (with r spect to the effective cross section) , increasing with fatigue life, fro one for low ycle fatigue tending to 1.42 for high cycl fa igue (N of about one million cycles). SEM analysis showed that fatigue crack initiated from the surface and propagated through th cross section, occurring in many cases multi-nucleation. © 2018 The Authors. Published by Elsevier B.V. Peer-review under espons bility of the ECF22 organizers. Abstract

© 2016 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of PCF 2016. Keywords: Additive manufacturing, Fatigue, Notch sensibility, TiAl6V4 alloy. Keywords: Additive manufacturing, Fatigue, Notch sensibility, TiAl6V4 alloy.

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 Authors. Published by Elsevier B.V. Peer review under r sponsibility of the ECF22 o ganizers. * Corresponding author. Tel.: +351239790200; fax: +351239790331. E-mail address: borrego@isec.pt * Corresponding author. Tel.: +351239790200; fax: +351239790331. E-mail ad ress: borrego@isec.pt

2452-3216 © 2016 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of PCF 2016.

2452-3216  2018 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the ECF22 organizers. 10.1016/j.prostr.2018.12.186