PSI - Issue 8

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 8 (2018) 354–367 Available online at www.sciencedirect.com ScienceDirect Structural Int grity 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 © 2018 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scien ific Committee of AIAS 2017 Int r ational Conference on Stress Analysis AIAS 2017 International Conference on Stress Analysis, AIAS 2017, 6-9 September 2017, Pisa, Italy Quantitative analysis of thermographic data through different algorithms E. D'Accardi; D. Palumbo; R. Tamborrino; U. Galietti Politecnico di Bari - Dipartimento di Meccanica, Matematica e Management, Viale Japigia 182, 70126 Bari, e-mail: ester.daccardi@poliba.it, davide.palumbo@poliba.it, rosanna.tamborrino@poliba.it, umberto.galietti@poliba.it. Abstract Pulsed thermography is commonly used as non-destructive technique for evaluating defects within materials and components. However, raw thermal imagi data are sually not suitable for quantitative evaluation of defects. It was necessary to process the raw thermal data acquired to obtain a series of satisfactory results for a correct and quantitative material evaluation. In the last years, many data processing algorithms have been developed and each of them provide enhanced detection and sizing of flaws. In this work, starting from the same brief pulsed thermographic test carried out on an aluminium specimen with twenty flat bottom holes of known nominal size, diff rent algori hms have been compared. The algorithms used have been: Pulsed Phase Thermography (PPT), Slope, Correlation Coeffici nt (R 2 ), Thermal Signal Reconstruction (TSR), Principal Component Analysis (PCT). By analysing the results obtained using different approaches, it was possible to focus on the advantages, disadvantages and sensitivity of the various thermographic algorithms implemented. © 2017 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of AIAS 2017 International Conference on Stress Analysis. Keywords: Pulsed thermography; Algorithm; PPT; PCT; TSR; R 2 ; Slope. AIAS 2017 International Conference on Stress Analysis, AIAS 2017, 6-9 September 2017, Pisa, Italy Quantitative analysis of thermographic data through different algorithms E. D'Accardi; D. Palumbo; R. Tamborrino; U. Galietti Polit cnico di Bari - Dipartimento di Meccanica, M tematica e Management, Viale Japigia 182, 70126 Bari, e-mail: ester.daccardi@poliba.it, davide.palumbo@poliba.it, rosanna.tamborrino@poliba.it, umberto.galietti@poliba.it. Abstract Pulsed thermography is commonly us d as non-destructive technique for evaluating defects within materials and components. However, raw ther al imaging data are usually not suitable for quantitative evaluation of defects. It was necessary to process the raw thermal data acquired to obtain a series of satisfactory results for a correct and quantitative material evaluation. In the last years, many data processing algorithms have been developed and each of them provide enhanced detection and sizing of flaws. In this work, starting from the same brief pulsed thermographic test carried out on an aluminium specimen with twenty flat bottom holes of known nominal size, different algorithms have been compared. The algorithms used have been: ulsed Phase Thermography (PPT), Slope, Correlat on Co ffici nt (R 2 ), Thermal Signal Recons ruction (TSR), Principal Component Analysis (PCT). By analysing the results obtained using different approaches, it was possible to focus on the advantages, disadvantages and sensitivity of the various thermographic algorithms implemented. © 2017 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of AIAS 2017 International Conference on Stress Analysis. Keywords: Pulsed thermography; Algorithm; PPT; PCT; TSR; R 2 ; Slope.

© 2016 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of PCF 2016. 1. Introductio .

1. Introduction.

Keywords: High Pressure Turbine Blade; Creep; Finite Element Method; 3D Model; Simulation. In the aeronautics field, during manufacturing process, random porosity or several defects may appear in mechanical structures. These undesirable defects affect the structure and its mechanical properties. In this regard, it is very important to check the integrity of the components to reveal these defects. Several non-destructive techniques can be used to detect such defects. In the aeronautics field, during manufacturing process, random porosity or several defects may appear in mechanical structures. These undesirable defects affect the structure and its mechanical properties. In this regard, it is very important to check the integrity of the components to reveal these defects. Several non-destructive techniques can be used to detect such defects.

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.2017.12.036