PSI - Issue 7

ScienceDirect Available online at www.sciencedirect.com Av ilable o line at ww.sciencedire t.com ScienceDirect Structural Integrity Procedia 00 (2016) 000 – 000 Procedia Structu al Integrity 7 (2017) 141–148 Available online at www.sciencedirect.com ScienceDirect Structural Integrity Procedia 00 (2017) 000–000 Available online at www.sciencedirect.com Sci nceDir t Structural Integrity Procedia 00 (2017) 000–000

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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 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.: +351 218419991. E-mail address: amd@tecnico.ulisboa.pt 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.2017.11.071 * Corresponding author. Tel.: +49 (0) 30 8104 1531; fax: +49 (0) 30 8104 1537. E-mail address: uwe.zerbst@bam.de * Corresponding author. Tel.: +49 (0) 30 8104 1531; fax: +49 (0) 30 8104 1537. E-mail address: uwe.zerbst@bam.de 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 Damage develop ent a d damage tol ranc of structures manufactured by sel ctive laser melting – a review U. Zerbst * and K. Hilgenberg Bundesanst lt für Materialforschung nd - rüfung (BAM) ter den Eich n 87, D-12205 Berlin, Germany Abstract The additive manufacturing technology of Selective Laser Melting (SLM) experiences a rapid development within an increasing marked of quite different application fields. The properties of SLM materials and structures are influenced by a number of tech nological parameters such as the metal powder (particle size, homogeneity, cleanliness), the laser tool (power, beam diameter, pulse lengths), the scanning operation (speed, sequence and orientation of melting paths), parameters of the over-all equipment (design and preheating of the base plate, currents and turbulence in the protective gas atmosphere) and, last not least, the hatching strategy including the build-up di ection of the structure with respect to the loa ing direction of the component. For the perspective use of SLM structures as load carrying, safety-relevant components the knowledge of their mechanical properties is necessary. It is essential to understand these in the context of the manufacturing-related features and at the back ground of the basic characteristics of metallic materials: crystal lattice, microstructure and material defects. The paper provides an overview on factors which affect the mechanical parameters stiffness, strength, ductility, toughness, fatigue crack propagation and fatigue strength in the context of selective laser melting. Keywords: F tigue strength; fractu e mechanics; initi l crack size; short crack propaga ion; multiple crack pr pagation Introduction Fig. 1 (a) gives an overview on the factors that influence the principal mechanical properties of metallic materials (stiffness, strength, ductility, toughness, fatigue crack propagation and fatigue strength). These properties are affected by the materials basic characteristics (crystal lattice, microstructure and material defects) in quite different ways. In the following sections a brief over view is provided on the potential relationships with special emphasis to structures manufactured by Selective Laser Melting (SLM). Because of its paramount importance, this shall be preceded by the definition of the build-up direction with respect to the applied 3rd International Symposium on Fatigue Design and Material Defects, FDMD 2017, 19-22 September 2017, Lecco, Italy Damage d velopment and damage tolerance of structures manufactured by selective laser melting – a review U. Zerbst * and K. Hilgenberg Bundesanstalt für Materialforschung und -prüfung (BAM), Unter den Eichen 87, D-12205 Berlin, Germany Abstract The additive manufacturing tech ology of Selective Laser Melting (SLM) exper enc s a rapid devel pment within an increa ing marked of quite different application fields. The properties of SLM materials and structures are influenced by a number of tech nological parameters such as t e metal powder (particle size, homogeneity, cleanliness), the laser t ol (power, beam diameter, pulse lengths), the scanni operati n (speed, sequence and orientation of melting paths), arameters of the over-all equipment (design and preheating of the base plate, currents and turbulence in the protective gas atmosphere) and, last not least, th hatching strategy including the build-up direction of the structure with respect to the loading direction of th component. For the perspective use of SLM structures as load carrying, safety-relevant components the knowledge of their mechanical properties is necessary. It is essential to understand these in the context of the manufacturing-related features and at the back ground of the basic characteristics of metallic materials: crystal lattice, microstructure and material defects. The paper provides an overvi w on fa tors which affect the mechanical parameters stiffness, strength, ductility, toughness, fatigue crack propagation and fatigue strength in the context of selective las r melting. Keywords: Fatigue strength; fracture mechanics; initial crack s ze; short crack p opagation; multiple crack propagation Introduction Fig. 1 (a) gives an overview on the factors that influence the principal mechanical properties of metallic materials (stiffness, strength, ductility, toughness, fatigue crack propagation and fatigue strength). These properties are affected by the materials basic characteristics (crystal lattice, microstructure and material defects) in quite different ways. In the following sections a brief over view is provided on th potential relationships with special emphasis to structures manufactured by Selective Laser Melting (SLM). Because of its paramount importance, this shall be preceded by the definition of the build-up direction with respect to the applied © 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.