PSI - Issue 8

ScienceDirect Available online at www.sciencedirect.com Av ilable o line at www.sciencedire t.com Sci ceDirect Structural Integrity Procedia 00 (2016) 000 – 000 Procedia Structu al Integrity 8 (2018) 288–296 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 Modelling of interactions between Barely Visible Impact Damages and Lamb waves in CFRP laminates. A. De Luca a *, G. Lamanna a , A. Soprano a , F. Caputo a a Department of Industrial and Information Engineering, University of Campania L. Vanvitelli, Via Roma 29, 81031 Aversa, Italy The improvement of the current design practice, especially for conventional materials, has allowed the production of structures able to better tolerat the prese ce of cracks and, in general, damages u d r the in-service loading conditions. As a result, especially in the aerospace field, nowadays, the damage tolerance philosophy is the core of the current design practice. However, conversely to the conventional materials, composite materials still cannot count on established prediction models supporting the damage tolerance approach. Among the critical damages which could affect composite materials, BVIDs (Barely Visible Impact Damages) due to accidental Low Velocity Impact (LVI) phenomena play a critical role. Since they cannot be easily detectable during the inspection intervals, in order to fulfil the damage tolerance targets, large safety factors are applied during the design current practice, resulting in the oversizing of the structure. For these reasons, Structural Health Monitoring (SHM) techniques are being widely used for the improvement of the current design practice, allowing the damage detection. Thanks to the possibility to assess the structural health during the in-service loading conditions, Lamb waves, among the several non destructive testing (NDT), appear to be the best candidate for damage detection. Studies on this topic are never enough and the literature cannot still count on a Finite Element (FE) procedure able to simulate Lamb wave propagation on LVI damaged plates. This work deals with a FE procedure, developed by using the FE code Abaqus v.6.14®, for the simulation of the interaction between ultrasonic guided waves and LVI damages in composite laminates, whose damages have been modelled by means of Hashin criteria in a previous impact simulation. © 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 Modelling of int ractions b tween Barely Visible Imp ct Damages and Lamb waves in CFRP laminates. A. De Luca a *, G. Lamanna a , A. Soprano a , F. Caputo a a Department of Industrial and Information Engineering, University of Campania L. Vanvitelli, Via Roma 29, 81031 Aversa, Italy Abstract Th improv ment of the curr nt design pr tice, especially for conventional materials, has allowed the pro uction of structures abl to better tol rate th prese ce of cracks and, in gener l, dam ges under the in-service loading conditions. As a r sult especially in the aerospace field, now days, the damage tolerance philos phy is the core of the current design practice. However, conversely to th conventional materials, composite materials still cannot ount on established prediction models supporting the da age tolerance pproach. Among the critical damages w ich could affect omposite materials, BVIDs (Bar ly Visibl Impact Damages) due to accidental Low Velocity Impact (LVI) phenome a pl y a critical rol . Sin e they cannot be easily detectable d ing the inspection intervals, in order to fulfil the da age t ler nc targets, large safety factors are applied during the design current practic , resulting in the ove sizing of the stru tu . For these reasons, Structural Health Monitoring (SHM) techniques are being widely u ed for the improvement of the current design practi e, allowing the damage detection. Thanks to the po sibility o assess the structu al h alth during the in-se vice loading conditions, Lamb waves, among the several non destructive testing (NDT), appear to be the best candidat for damage detection. Studies on this topic are never enou h and the literature cannot still count on a Finite Element (FE) procedure able t simulate Lamb wave propagation on LVI damaged plates. This work deals with a FE procedure, developed by using the FE code Abaqus v.6.14®, for the simulati n of the interaction between ultraso ic guided waves and LVI damages in composite laminates, whose damages have been modelled by means of Hashin criteria in a previous impact simulation. © 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: Lamb waves; SHM; LVI; Composite Materials; Non-destructive testing; FE simulation Keywords: Lamb waves; SHM; LVI; Composite Materials; Non-destructive testing; FE si ulation Keywords: High Pressure Turbine Blade; Creep; Finite Element Method; 3D Model; Simulation. Abstract

* Corresponding author. Tel.: +0815010318; E-mail address: alessandro.deluca@unicampania.it * Correspon ing author. Tel.: +0815010318; E-mail address: alessandro.deluca@unicampania.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.2017.12.030