PSI - Issue 8

ScienceDirect Available online at www.sciencedirect.com Av ilable o line at ww.sciencedire t.com cienceDirect Structural Integrity Procedia 00 (2016) 000 – 000 Procedia Structu al Integrity 8 (2018) 345–353 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. AIAS 2017 International Conference on Stress Analysis, AIAS 2017, 6-9 September 2017, Pisa, Italy A study on the dynamic structural behavior of Olympic sabres F. Vivaldi a , L. Cortese b *, T. Coppola c , A. Mazzarano c , F. Nalli d a Sapienza University of Rome, Italy b Department of Aerospace and Mechanical Engineering, Sapienza University of Rome, Italy. c Rina Consulting - Centro Sviluppo Materiali (CSM), Via di Castel Romano, Rome, Italy. d Faculty of Science and Technology, Free University of Bolzano-Bozen, Bolzano, Italy. Abstract Sabres used in Olympic fencing are subject to severe elastic deformations during matches and training sessions. Even though strict rules for their manufacturing are prescribed by he international fencing federation, with requirements in terms of geometrical constraints and material (steel) properties, nonetheless frequent unexpected ruptures are observed. These may cause injuries to the fencers, and involve the replacement of the blade. In this study an experimental-numerical approach is adopted to investigate the underlying failure mechanisms. To this purpose, several attacks, “bouts” in fencing, were live filmed during actual practice with digital cameras and a trajectory tracking analysis was performed on the most critical of them, taking advantage of markers fixed on the blades at different positions. The post-processed data were subsequently used as boundary conditions of a 3D finite element model of the blade. Running a non-linear transient analysis, global and local quantities such as maximum stored elastic energy, stress and strain states, strain rates and possible permanent plastic strains were evaluated. A validati n of the FE model with experiments was also carried out. From the critical analysis of experi ental and numerical results it was possibl to speculate about e influence of materials and dynamic related e fects on the structural behavior of the blade. Ev ntually, hypotheses o fracture mechanisms were formulated. © 2017 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of AIAS 2017 International Conference on Stress Analysis. AIAS 2017 International Conference on Stress Analysis, AIAS 2017, 6-9 September 2017, Pisa, Italy A study on the dynamic structural behavior of Olympic sabres F. Vivaldi a , L. Cortese b *, T. Coppola c , A. Mazzarano c , F. Nalli d a Sapienz University of Rome, Italy b Departme t of Aerospace and Mechanical Engineering, S p enza University of Rome, Italy. c Rina Consulting - Ce tro Sviluppo Materiali (CSM), Via di Castel Roman , Rome, Italy. d Faculty of Science and Technology, Free University of Bolzano-Bozen, Bolzano, Italy. Abstract Sabres used in Olympic fencing are subject to severe elastic deformations during matches nd training sessions. Eve though strict rul s for their m nufacturing r prescribed by th international f ncing federation, with requirem nts in terms of geom trical on traints and material (steel) properties, non theless frequent unexpected ruptures are obs rved. These may c use injuries to the fe c rs, nd involv the replac ment of the blade. In this study an experimental-numerical approach is adopted to investigate the underlying failure mechanisms. To this purpose, several tt cks, “bouts” in fencing, were live filmed during actual practice with digital cameras and a trajectory tracking analysis was performed on the most critical of them, taking adva tage of markers fixed on the blades at different positions. The post-pr cessed dat w re subsequently used as bound ry conditions of a 3D finite element model of the blade. Run ing a non-li ear transient analysis, global and lo al quantities such as maximum stored elastic energy, stress and strai tate , strain at s and possible pe manent pla tic strains were evaluated. A validation of the FE model with xperim nts was also carri d ut. From the critical analysis of exp rimental and n merical results it was possible to speculate about the influence of mat rials and dyna ic related effects on the structural behavior of the blade. Eventually, hypotheses n fracture mechanis s were formulated. © 2017 The Autho s. Publ shed by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of AIAS 2017 International Conference on Stress Analysis. © 2016 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of PCF 2016. Copyright © 2018 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of AIAS 2017 International Conference on Stress Analysis Keywords: Olympic sabres; Trajectory tracking; FE Analysis; Damage assessment;

Keywords: High Pressure Turbine Blade; Creep; Finite Element Method; 3D Model; Simulation. Keywords: Olympic sabres; Trajectory tracking; FE Analysis; Damage assessment;

* Corresponding author. Tel.: +39 6 44585236; fax: +39 6 44585250. E-mail address: luca.cortese@uniroma1.it * Correspon ing author. Tel.: +39 6 44585236; fax: +39 6 44585250. E-mail address: luca.cortese@uniroma1.it

2452-3216 © 2017 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of AIAS 2017 International Conference on Stress Analysis. 2452 3216 © 2017 Th Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of AIAS 2017 International 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 Copyright  2018 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of AIAS 2017 International Conference on Stress Analysis 10.1016/j.prostr.2017.12.035