PSI - Issue 12

ScienceDirect Available online at www.sciencedirect.com Av ilable o line at ww.sciencedire t.com ScienceDirect Structural Integrity Procedia 00 (2016) 000 – 000 Procedia Structu al Integrity 12 (2018) 448–456 Available online at www.sciencedirect.com Structural Integrity Procedia 00 (2018) 000–000 Available online at www.sciencedirect.com Structural Integrity Procedia 00 (2018) 000–000

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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.2018.11.073 ∗ Corresponding author. Tel.: + 39-06-7259-7143 E-mail address: Corrado.groth@uniroma2.it 2210-7843 c 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. ∗ Corresponding author. Tel.: + 39-06-7259-7143 E-mail address: Corrado.groth@uniroma2.it 2210-7843 c 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 r ponsibility of the Scientific ommitt e of AIAS 2018 International Conference on Stress Analysis. * Corresponding author. Tel.: +351 218419991. E-mail address: amd@tecnico.ulisboa.pt Verification and validation is an essential mean to evaluate performance and reliability of computational tools. By assessing how accurately computational results compare with experimental data it is possible to investigate not only the accuracy but also the limits of the models, making experimental campaigns fundamentals to attest the trustworthi ness of the tools in a modeling-and-simulation-based design scenario. While engineers are nowadays confident on the Verification and validation is an essential mean to evaluate performance and reliability of computational tools. By assessing how accurately computational results compare with experimental data it is possible to investigate not only the accuracy but also the limits of the models, making experimental campaigns fundamentals to attest the trustworthi ness of the tools in a modeling-and-simulation-based design scenario. While engineers are nowadays confident on the 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 2018 International Conference on Stress Analysis Structural validation of a realistic wing structure: the RIBES test article Corrado Groth a, ∗ , Stefano Porziani a , Andrea Chiappa a , Francesco Giorgetti a , Ubaldo Cella a , Fabrizio Nicolosi b , Pierluigi Della Vecchia b , Franco Mastroddi c , Giuliano Coppotelli c , Marco Evangelos Biancolini a a University of Rome ”Tor Vergata”, 00133 Rome, Italy b University of Naples ”Federico II”, 80125 Naples, Italy c University of Rome ”La Sapienza”, 00184 Rome, Italy Abstract Several experimental test cases are available in literature to study and validate fluid structure interaction methods. They, however, focus the attention mainly on replicating typical cruising aerodynamic conditions forcing the adoption of fully steel made models able to operate with the high loads generated in high speed facilities. This translates in a complete loss of similitude with typical realistic aeronautical wing structures configurations. To reverse this trend, and to better study the aerolastic mechanism from a structural point of view, an aeroelastic measurement campaign was carried within the EU RIBES project. A half wing model for wind tunnel tests was designed and manufactured replicating a typical metallic wing box structure, producing a database of loads, pressure, stress and deformation measurements. In this paper the design, manufacturing and validation activities performed within the RIBES project are described, with a focus on the structural behavior of the test article. All experimental data and numerical models are made freely available to the scientific community. c 2018 The Authors. Published by Elsevier B.V. This is an open access article u d r the CC BY-NC-ND license (http: // creativecommons.org / licenses / by-nc-nd / 3.0 / ) Peer-review under responsibility of the Scientific Committe of AIAS 2018 Internation l Conference on Stress Analysis. Keywords: FSI; Experimental Validation; Structural Validation; CFD; CSM © 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 Structural validation of a realistic ing structure: the RIBES test article Corrado Groth a, ∗ , Stefano Porziani a , Andrea Chiappa a , Francesco Giorgetti a , Ubaldo Cella a , Fabrizio Nicolosi b , Pierluigi Della Vecchia b , Franco Mastroddi c , Giuliano Coppotelli c , arco Evangelos Biancolini a a University of Rome ”Tor Vergata”, 00133 Rome, Italy b University of Naples ”Federico II”, 80125 Naples, Italy c University of Rome ”La Sapienza”, 00184 Rome, Italy Abstract Several experimental test cases are available in literature to study and validate fluid structure interaction methods. They, however, focus the attention mainly on replicating typical cruising aerodynamic conditions forcing the adoption of fully steel made models able to operate with the high loads generated in high speed facilities. This translates in a complete loss of similitude with typical realistic aeronautical wing structures configurations. To reverse this trend, and to better study the aerolastic mechanism from a structural point of view, an aeroelastic measurement campaign was carried within the EU RIBES proj ct. A half wing model for wind tunnel tests was designed and manufactured replicating a typical metallic wing box structure, producing a databa e of loads, pressure, stress and deforma ion measur m nts. In this paper th design, manufacturing and validation activiti s perfor ed within the RIBES pr ject are described, with a focus on the structural behavior of the test article. All experimental data and numerical models a e made fre ly available to the scient fic com unit . c 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 / ) er-review unde responsibility of the Scientific Committee of AIAS 2018 International Conference on Stress Analysis. Keywords: FSI; Experimental Validation; Structural Validation; CFD; CSM © 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. 1. Introduction 1. Introduction