PSI - Issue 5

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 5 (2017) 468–475 Available online at www.sciencedirect.com 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. 2nd International Conference on Structural Integrity, ICSI 2017, 4-7 September 2017, Funchal, Madeira, Portugal On the Non-linear Elasto-Plastic Behavior of AA6061-T6: Experim ntal and Numerical Implementations Behzad V. Farahani a,b, *, Jorge Belinha a,b , Paulo J. Tavares a , P. M. G. P. Moreira a a INEGI, Institute of Science and Innovation in Mechanical and Industrial Engineering, Dr. Roberto Frias Street, 400, 4200-465, Porto, Portugal. b FEUP, Faculty of Engineering, University of Porto, Dr. Roberto Frias Street, 4200-465, Porto, Portugal. Abstract In this study, using an elasto-plastic constitutive model, the structural response of an Aluminium alloy AA6061 T6 bi-failure specimen is investigated. The mechanical specifications and material model are fully defined. It is intended to evaluate the force variation versus the displacement field during a tensile loading test. Digital Image Correlation (DIC) approach is used to acquire the experimental data. Afterwards, a 2D model is analysed through Finite Element (FE) formulation considering an isotropic elasto-plastic regime and the obtained results are compared to DIC outcome. A reasonable agreement between numerical and experimental results was found. Additionally, the problem is numerically solved using the Natural Neighbour Radial Point Interpolation Meshless method (NNRPIM) formulation assuming an elasto-plastic behaviour for the material. An elasto-plastic return- apping routine is defined based on von-Mises yield criteria to evaluate the stress tensor in a pseudo-time stepping scheme, which imposes displacements. Taking into account the non-linear system of equations, a non-linear Newton-Raphson algorithm is used to obtain the converged solution. The NNRPIM results have a reasonable agreement compared to the DIC solution. The obtained results imply that the proposed elasto-plastic NNRPIM procedure is feasible and robust. © 2017 The Authors. Published by Elsevier B.V. Peer-review under responsibil ty of the Scientific Committee of ICSI 2017. 2nd International Conference on Structural Integrity, ICSI 2017, 4-7 September 2017, Funchal, Madeira, Portugal On the Non-linear Elasto-Plastic Behavior of AA6061-T6: Experimental and Numerical Implementations Behzad V. Farahani a,b, *, Jorge Belinha a,b , Paulo J. Tavares a , P. M. G. P. Moreira a a INEGI, Institute of Science and Innov t on in Mechanical nd Ind strial E gine ri g, Dr. Roberto Frias Street, 400, 4200-465, Porto, Po tugal. b FEUP, Faculty of Engineering, University of Porto, Dr. Roberto Frias Street, 4200-465, Porto, Portugal. Abstract In this study, using an elasto-pl stic constitutive model, the structural response of an Aluminium alloy AA6061 T6 bi-failure specimen is investigated. The mec anical specifications and material model are fully defined. It is intended to evaluate the force variati n versus the displac ment field during a tensile loading test. Digital Ima e Corr lation (DIC) app oach is used to acquire the ex erimental data. Afterwards, a 2D model is analysed through Finite Element (FE) formulation considering an isotropic elasto-plastic regime and the obtained results are compared to DIC outco e. A reasonable agreem nt between numerical and experimental results was found. Additionally, the problem is numerically solved using the Natural Neighbour Radial Point Interpolation Meshless method (NNRPIM) formulation assuming an elasto-plastic behaviour for the material. An elasto-plastic return-mapping routine is defin d based on von-Mises yield criteria to evaluate the stress tensor in a p eudo-time stepping scheme, which impose displacements. Taking into account the non-linear system of equations, a non-line r Newton-Raphson algorithm is used to obtain the converged solution. The NNRPIM results have a reasonable agre ment comp red to the DIC solution. The obtained results imply that the proposed elasto-plastic NNRPIM procedure is feasible and robust. © 2017 The Autho s. Publ shed by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of ICSI 2017. © 2017 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of ICSI 2017

© 2016 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of PCF 2016. Keywords: Non-linear Elasto-pla tic; Finite Elem nt Method; Digital Image Correlation; NNRPIM, Bi-failure. Keywords: Non-linear Elasto-plastic; Finite Element Method; Digital Image Correlation; NNRPIM, Bi-failure.

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

* Corresponding author. Tel.: +351 225082151. E-mail address: behzad.farahani@fe.up.pt * Correspon ing aut or. Tel.: +351 225082151. E-mail address: behzad.farahani@fe.up.pt

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 ICSI 2017 10.1016/j.prostr.2017.07.145 * Corresponding author. Tel.: +351 218419991. E-mail address: amd@tecnico.ulisboa.pt 2452 3216 © 2017 Th Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of ICSI 2017. 2452-3216 © 2017 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of ICSI 2017.