PSI - Issue 7

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 7 (2017) 248–253 Structural Integrity Procedia 00 (2017) 000–000 Available online at www.sciencedirect.com ScienceDirect Structural Integrity Procedia 00 (2017) 000–000 ScienceDirect

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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. Copyright © 2017 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of the 3rd International Symposium on Fatigue Design and Material Defects. 3rd International Symposium on Fatigue Design and Material Defects, FDMD 2017, 19-22 September 2017, Lecco, Italy Fatigue behaviour of age-hardened Cu-Ni-Si alloy and effect of sporadic dis ontinuous precipitates on f tigue strength M. Goto a, *, S.Z. Han b , T.Yamamoto a , J. Kitamura a , J.H. Ahn b , T. Iwamura a , S.H. Lim c a Department of Mechanical Engineering, Oita University, Oita, 870-1192, Japan b Korea Institute of Materials Science, Changwon, 624-831, Republic of Korea c Kangwon National University, Chuncheon 200-701, Republic of Korea Abstract Microstructure and fatigue strength of Cu-Ni-Si alloy with high solute concentrations were studied. The maximum hardness of this alloy was obtained by 0.5 h aging (500°C) and the matrix was strengthened by nano-size δ -Ni 2 Si precipitates. In addition, some parts of grains transformed into discontinuous precipitates which bring a detrimental effect on mechanical properties, producing a sporadic distribution of discontinuous precipitates. The fatal cracks, which led to the fracture of the specimen, were initiated at the grain boundaries, not at discontinuous precipitation phases. The physical background of fatigue damage is discussed in light of the role of microstructure on the behaviour of fatigue cracks. © 2017 The Aut ors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of the 3rd International Symposium on Fatigue Design and Material Defects. Keywords: Fatigue; Copper alloy; Crack initiation; Micrstuructur 1. Introduction Cu alloy has been used for electric/el ctronic devices because of their superior combined property of strength and electric cond ctivity. Among Cu system alloys, Cu-Be alloy has high strength and high electric conductivity. 3rd International Symposium on Fatigue Design and Material Defects, FDMD 2017, 19-22 September 2017, Lecco, Italy Fatigue behaviour f age-hard ned Cu-Ni-Si alloy and effe t of sporadic discontinuous precipitates on fatigue strength M. Goto a, *, S.Z. Han b , T.Yamamoto a , J. Kitamura a , J.H. Ahn b , T. Iwamura a , S.H. Lim c a Department of Mechanical Engineering, Oita University, Oita, 870-1192, Japan b Korea Institute of Materials Science, Changwon, 624-831, Republic of Korea c Kangwon National University, Chuncheon 200-701, Republic of Korea Abstract Microstructure and atigue strength f Cu-Ni-Si alloy with high solute conc ntrations were studied. The maximum hardness of this all y was obtained by 0.5 h ag g (500°C) and the matrix was strengthened by nano-size δ -Ni 2 Si pr ipitates. In addition, som parts of grains tra sformed into discontinuous preci it t w ich bring a detrimental e fec on mech nical properties, producing a sporadic distrib tion of discontinuous precipitates. The fatal cracks, which led to the fracture of the specimen, were initiated at the grain boundar es, not at discontinuous precipitatio phases. The physical a kground of fatigue damage is discussed light of he role of microstructure on the behaviour of fatigue cracks. © 2017 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of the 3rd Internatio al Symposium on Fatigue Design and Material D fects. Keywords: Fatigue; Copper alloy; Crack initiation; Micrstuructur 1. Introduction Cu alloy has been used for electric/electronic devices because of their superior combined property of strength and electric conductivity. Amo g Cu system alloys, Cu-Be alloy has high strength and high electric conductivity. © 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.: +81-97-554-7772; fax: +81-97-554-7764. E-mail address: masagoto@oita-u.ac.jp

2452-3216 © 2017 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of the 3rd International Symposium on Fatigue Design and Material Defects. 2452-3216 © 2017 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of the 3rd International Symposium on Fatigue Design and Material Defects. * Corresponding author. Tel.: +81-97-554-7772; fax: +81-97-554-7764. E mail address: masagot @oita-u.ac.jp

* 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 PCF 2016.

2452-3216 Copyright  2017 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of the 3rd International Symposium on Fatigue Design and Material Defects. 10.1016/j.prostr.2017.11.085