PSI - Issue 7

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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 Structural Integrity 7 (2017) 92–10 ScienceDirect Structural Integrity Procedia 00 (2017) 000–000 Available online at www.sciencedirect.com ScienceDirect Structural Integrity Procedia 00 (2017) 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. Copyright © 2017 The Auth rs. Publish d by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of the 3rd I ternational Sympos um on Fatigue Desig and Material Defects. 3rd International Symposium on Fatigue Design and Material Defects, FDMD 2017, 19-22 September 2017, Lecco, Italy As-built surface layer characterization and fatigue behavior of DMLS Ti6Al4V R. Konečná a* , G. Nicoletto b , S. Fintová c , M. Frkáň a a Uuniversity of Zilina, Univerzitna 1,01026 Zilina, Slovakia b University of Parma, Parco Area delle Scienze 181/A, Italy c Institue of Physics of Materials, Zizkova 22, 61662 Czech Republic Abstract Direct Metal Laser Sintering (DMLS) is a powder bed fusion technology used in the fabrication layer-by-layer of metallic parts directly from a CAD file. Since the fatigue b havior of DMLS Ti6Al4V is strongly influenced by the surface roughness of the as built surface, fatigue tests were performed on smooth specimens produced with different orientations with respect to build using an EOS M 290 system. A SEM investigation and roughness measurements of the test surfaces were used to interpret the surface roughness as the contribution of i) roughness induced due to solidification of the melt pool (primary roughness); ii) roughness induced by partly melted powder particles (secondary roughness). Surface roughness modification from the as-built state by manual grinding was also investigated in fatigue and found to give a limited improvement. On the other hand, surface machining improves considerably the fatigue strength with respect to both the as-built condition and the manually ground 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: Ti6Al4V, direct metal laser sintering, heat treatments, fatigue, roughness, defects 3rd International Symposium on Fatigue Design and Material Defects, FDMD 2017, 19-22 September 2017, Lecco, Italy As-built surface lay r ch racterization and fatigue behavior of DMLS Ti6Al4V R. Konečná a* , G. Nicoletto b , S. Fintová c , M. Frkáň a a U niversity of Zilin , Univerz tna 1,0102 Zilina, Slovakia b University of Parma, Parco Area delle Scienze 181/A, Italy c Institue of Physics of Materials, Zizkova 22, 61662 Czech Republic Abstract Direct Metal Laser Sintering (DMLS) is a powder bed fusion technology used in the fabrication layer-by-layer of metallic parts directly from a CAD file. Since the fati ue behavior of DMLS Ti6Al4V is strongly influenced by the surface roughness of the as built surface, fatigue tests were performed on smooth specimens produced with different rientations with respect to build using an EOS M 290 s stem. A SEM investigation and roughness measurements of the test surfaces were used to interpret the surface roughness as the contribution of i) roughness induced due t solidification of the melt pool (primary roughness); ii) rough ess induced by partly melted powder p rticles (secondary roug ness). Surface roughness modification from the as-built state by manual grinding was also investigated in fatigue and found to give a limited improvement. On the other hand, surface machining improves considerably the fatigue strength with respect to both the as-built condition and the manually ground 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: Ti6Al4V, direct metal laser sintering, heat treatments, fatigue, roughness, defects

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

* Corresponding author. E-mail address: radomila.konecna@fstroj.uniza.sk * Corresponding author. E-mail address: radomila.konecna@fstroj.uniza.sk

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.2017.11.065

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