PSI - Issue 7

First page Table of contents Previous page 367 Next page Last page

ScienceDirect Available online at www.sciencedirect.com Av ilable o line at ww.sciencedire t.com ienceDirect Structural Integrity Procedia 00 (2016) 000 – 000 Procedia Structu al Integrity 7 (2017) 133–14 Structural Integrity Procedia 00 (2017) 000–000 Available online at www.sciencedirect.com ScienceDirect Structural Integrity Procedia 00 (2017) 000–000 ScienceDirect

www.elsevier.com/locate/procedia

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 Influence of post fabrication heat treatments on the fatigue behavior of Ti-6Al-4V p oduced by selective laser melting Gianni Nicoletto 1 , Stefania Maisano 2 *, Michele Antolotti 2 , Filippo Dall’Aglio 1 1 University of Parma, Dept. of Engineering and Architecture, 43124 Parma, Italy 2 BEAM-IT srl, Strada Prinzera, Fornovo Taro – Italy Abstract Selective Laser Melting (SLM) is ch racterized by a layer-wis buildi g process that enables the near net hape production of parts with a high geometrical complexity. The SLM process leads to the build-up of thermal stresses, while the rapid solidification leads to segregation phenomena and the development of non-equilibrium phases. To reduce thermal stresses and to optimize the microstructure and the mechanical properties for the specific application, suitable post-production heat treatments should be defined. Four different heat treatments in vacuum of SLM Ti6Al4V were investigated in relation to the fatigue behavior. Tensile and fatigue specimens were produced with a SLM system using the optimized process parameters. Microstructures before and after heat treatment were characterized by metallographic methods. Two post fabrication heat treatments are promising in terms of fatigue strength of as-built SLM Ti6Al4V. The role of surface machining was also investigated for one heat treatment condition. © 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. Keywords: Fatigue, Ti-6Al-4V, selective laser melting, heat treatments 3rd International Symposium on Fatigue Design and Material Defects, FDMD 2017 19-22 September 2017, Lecco, Italy Influence of post fabricati n heat treatments on the fatigue behavior f Ti-6Al-4V produced by selective laser melting Gianni Nicoletto 1 , Stefania Maisano 2 *, Michele Antolotti 2 , Filippo Dall’Aglio 1 1 University of Parma, Dept. of Engineering and Architecture, 43124 Parma, Italy 2 BEAM-IT srl, Strada Pri zera, Fornovo Taro – Italy Abstract Selective Laser Melting (SLM) is characterized by a layer-wise building process that enables the near net shape production of parts with a high geometrical complexity. The SLM process leads to the build-up of thermal stresses, while the rapid solidification leads to segregation phenomena and the development of non-equilibrium phases. To reduce thermal stresses and to optimize the microstructure and the mechanical properties for the specific application, suitable post-production heat treatments should be defined. Four different heat treatments in vacuum of SLM Ti6Al4V were investigated in relation to the fatigue behavior. Tensile and fatigue specimens were produced with a SLM system using the optimized process parameters. Microstructures before and after heat treatment were characterized by metallographic methods. Two post fabrication heat treatments are promising in terms of fatigue strength of as-built SLM Ti6Al4V. The role of surface machining was also investigated for one heat treatment condition. © 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 D fects.

Keywords: Fatigue, Ti-6Al-4V, selective laser melting, heat treatments

Keywords: High Pressure Turbine Blade; Creep; Finite Element Method; 3D Model; Simulation.

* Corresponding author. Tel.: +39 0525 401281 ; fax: +39 0525 406949 . E-mail address: s.maisano@beam-it.eu * Corresponding author. Tel.: +39 0525 401281 ; fax: +39 0525 406949 . E-mail address: s.maisano@beam-it.eu

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.2017.11.070

Made with FlippingBook Annual report maker