PSI - Issue 12

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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. © 2018 The Authors. Published by Elsevier B.V. This is an open access article under the CC BY-NC-ND license (http://creativecommons.org/licenses/by-nc-nd/3.0/) Peer-review under responsibility of the Scientific Committee of AIAS 2018 International Conference on Stress Analysis. AIAS 2018 International Conference on Stress Analysis Preliminary investigation on impact resistance of additive manufactured Ti-6Al-4V Gabriel Testa a, * and Gianluca Iannitti a a Università di Cassino e del lazio Meridionale, Via G. Di Biasio 43, Cassino 03043, Italy Abstract Understanding key failure mechanisms and material anomalies is one of the main challenges for an accelerated certification of additive manufactured parts. In this paper, the response to high velocity impact of Ti-6Al-4V printed by direct metal laser sintering was investigated and compared with wrought material. Taylor impact test at different impact velocities were performed with the scope to determine the velocity at onset damage development. Results show that such velocity is 57% lower than that of wrought material. Microscopy investigation on recovered samples reveals that the presence of initial voids in the microstructure, resulting from the printing process, reduces the shear resistance anticipating the formation of shear bands that is the main mechanism controlling fracture at high deformation rates. © 2018 The Aut ors. Published by Elsevier B.V. This is an open access article under the CC BY-NC-ND license (http://creativecommons.org/licenses/by-nc-nd/3.0/) Peer-review under responsibility of the Scientific Committee of AIAS 2018 International Conference on Stress Analysis. Keywords: additive manufacturing, impact, Ti-6Al-4V, Taylor cylinder test 1. Introduction Additive manufacturing technologies enable the construction of components in a near-net-shape condition by means of material layer-by-layer deposition using 3D model information. With particular reference to aero-space market, these technologies will drive a significative reduction of raw materials for the production of components in service AIAS 2018 International Conference on Stress Analysis Preliminary investigation on impact resistance of additive manufactured Ti-6Al-4V Gabriel Testa a, * and Gianluca Iannitti a a Università di Cassino e del lazio Meridionale, Via G. Di Biasio 43, Cassino 03043, Italy Abstract Understanding key failure mechanisms and material anomalies is one of the main challenges for an accelerated certification of additive manufactured parts. In this paper, the response to high velocity impact of Ti-6Al-4V printed by direct metal laser sintering was investigated nd compar d with wrought material. Taylor impact test at different impact velocities were performed with the scope to determine the velocity at onset damage development. Results show that such velocity is 57% lo er than that of rought material. Microscopy investigation on recovered samples reveals that the presence of initial voids in the microstructure, resulting from the printing process, reduces the shear resistance anticipating the formation of shear bands that is the main mechanism controlling fracture at high deformation rates. © 2018 The Authors. Published by Elsevier B.V. This is an open access article under the CC BY-NC-ND license (http://creativecommons.org/licenses/by-nc-nd/3.0/) Peer-review under responsibility of the Scientific Committee of AIAS 2018 International Conference on Stress Analysis. Keywords: additive manufacturing, impact, Ti-6Al-4V, Taylor cylinder test 1. Introduction Additive manufacturing technologies enable the construction of components in a near-net-shape condition by means of material layer-by-layer deposition using 3D model information. With particular reference to aero-space market, these technologies will drive a significative reduction of raw materials for the production of components in service © 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.: +39-0776-2993693; fax:+39-0776-2993390. E-mail address: gabriel.testa@unicas.it * Corresponding author. Tel.: +39-0776-2993693; fax:+39-0776-2993390. E-mail address: gabriel.t sta@unicas.it

2452-3216 © 2018 The Authors. Published by Elsevier B.V. This is an open access article under the CC BY-NC-ND license (http://creativecommons.org/licenses/by-nc-nd/3.0/) Peer-revi w u er responsibility of the Scientific Committee of AIAS 2018 International Conference on Stress Analysis. 2452-3216 © 2018 The Authors. Published by Elsevier B.V. This is an open access article under the CC BY-NC-ND license (http://creativecommons.org/licenses/by-nc-nd/3.0/) Peer-review u der responsibility of t Scientific ommittee of AIAS 2018 Internati al Conference on Stress Analysis.

* 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  2018 The Authors. Published by Elsevier B.V. This is an open access article under the CC BY-NC-ND license (http://creativecommons.org/licenses/by-nc-nd/3.0/) Peer-review under responsibility of the Scientific Committee of AIAS 2018 International Conference on Stress Analysis. 10.1016/j.prostr.2018.11.060