PSI - Issue 12

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 12 (2018) 578–588 Available online at www.sciencedirect.com ScienceDirect Structural Integrity Procedia 00 (2018) 000 – 000 ScienceDirect Structural Integrity Procedia 00 (2018) 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 2018 International Conference on Stress Analysis A sensitivity analysis on the damage detection capability of a Lamb waves based SHM system for a composite winglet A. De Luca a *, D. Perfetto a , A. De Fenza b,c , G. Petrone b , F. Caputo a a Department of Engineering, University of Campania “L. Vanvitelli”, Via Roma 29, 81031 Aversa, Italy b Department of Industrial Engineering – Aerospace Division, Università degli Studi di Napoli “Federico II”, Via Claudio 21, 80125, Napoli, Italy c Department of Bioengineering and Aerospace Engineering, Universidad Carlos III de Madrid, Av. de la Universidad 30, 28911 Leganés, Spain Lamb waves based Structural Health Monitoring (SHM) systems, thanks to their high sensitivity to damage detection and the ability to travel over a long distance with low power consumption, are founding increasing industrial applications, especially in the aerospace field, where airworthiness authorities require that composite materials in primary structures must remain undamaged during the in-service life. In order to tolerate damage and monitor its severity and, consequently, to repair the structure only when strictly needed, the use of SHM systems appears to be an efficient solution providing benefits for the current design practice. The continuous assessment of the structural i tegrity, which can be accomplishe by SHM systems, can play a key-role to ac ieve a less-conservative design as well as to facil tate m intenanc operations. This p per deals with a sensitivity analysis, based on the Finite Ele nt (FE) theory, aimed to investigate numerically the influence of the damage orientation on the dam ge d tection capability of a Lamb waves based SHM system arranged on a damaged Glass Fiber Reinf rced Poly er composite winglet. Damage detection sensitivity has been measured by analyzing the interaction between the modelled damages and guided waves under a specific central frequency. Signals recorded at different locations by piezoelectric sensors have been compared with the baseline signals achieved under a pristine configuration of the winglet by means of a damage index. A specific trend of the considered damage index has been found out as function of the damage orientation. © 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. © 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 respon ibility of the Scientifi Committee of AIAS 2018 International Conference on Stress Analysis. AIAS 2018 International Conference on Stress Analysis A sensitivity analysis on the damage detection capability of a Lamb waves based SHM system for a composite winglet A. De Luca a *, D. Perfetto a , A. De Fenza b,c , G. Petrone b , F. Caputo a a Department of Engineering, University of Campania “L. Vanvitelli”, Via Roma 29, 81031 Aversa, Italy b Department of Industrial Engineering – Aerospace Division, Università degli Studi di Napoli “Federico II”, Via Claudio 21, 80125, Napoli, Italy c Department of Bioengineering a d Aerospace Engineering, Universidad Carlos III de Madrid, Av. la Universidad 30, 289 1 Leganés, Spain Abstract Lamb waves based Structural Health Monitoring (SHM) systems, thanks to their high sensitivity to damage detection and the ability to travel over a long distance with low power consumption, are founding increasing industrial applications, especially in the aerospace field, where airworthiness authorities require that composite materials in primary structures must remain undamaged during the i -service life. In rder to tolerate damage and monitor its severity and, consequently, to r p ir the structu e only wh n strictly needed, t e u e of SHM systems appears to be an efficient solution roviding benefits for the current design practice. The continuous assessment of the structural integrity, which can be accomplishe by SHM systems, can play a key-role t achieve a less-co s rvative de ign as well a to facilitate maintenance operati ns. This paper deals with a sensitivity analysis, bas d n the Finite Element (FE) theo y, aimed to investigate numeri ally the influen e of t e damag ori ntation on the damage dete tion c pability of a Lamb waves base SHM s st m arranged o a damage Glass Fiber Reinforced Polymer composite winglet. Da age d tection sensitivity has be n measured by analyzing t i teraction between the mod lled damages and guided waves under a specific central frequency. ignals rec rded at different locations by piezoelectric sensors have been compared with the baselin signals achie ed under a pristine configuration of t winglet by means of a damage in ex. A pecific tren of the considered damag index has been fou d out as function of the damage orientation. © 2018 Th 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 esponsibility of the Scientific Committee of AIAS 2018 International Conference on Stress Analysis. © 2016 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of PCF 2016. Abstract

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

* Corresponding author. Tel.: +39 081 5010 318 E-mail address: alessandro.deluca@unicampania.it * Corresponding author. Tel.: +39 081 5010 318 E-mail address: alessandro.deluca@unicampania.it

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.2018.11.061 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-revi w u er responsibility of the Scientific Committee of AIAS 2018 International Conference on Stress Analysis. 2452-3216 © 2018 Th Authors. P blished 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.: +351 218419991. E-mail address: amd@tecnico.ulisboa.pt