PSI - Issue 5

ScienceDirect Available online at www.sciencedirect.com Av ilable o line at ww.sciencedire t.com ienceDirect Structural Integrity Procedia 00 (2016) 000 – 000 Procedia Structu al Integrity 5 (2017) 729–736 Available online at www.sciencedirect.com ScienceDirect Structural Integrity Procedia 00 (2017) 000 – 000 il l li t . i ir t. tructural Integrity rocedia 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. 2nd International Conference on Structural Integrity, ICSI 2017, 4-7 September 2017, Funchal, Madeira, Portugal Structural health monitoring on an unmanned aerial vehicle wing’s beam based on fiber Bragg gratings and pattern recognition techniques Alejandro Carvajal-Castrillón a *, Joham Alvarez-Montoya a , Juliana Niño-Navia a , Leonardo Betancur-Agudelo b , Ferney Amaya-Fernández b , and Julián Sierra-Pérez a a Grupo de Investigación en Ingeniería Aeroespacial (GIIA), Universidad Pontificia Bolivariana, Circular 1-70-01, Medellín 050031, Colombia b Grupo de Investigación, Desarrollo y Aplicación e Telecomunicaciones e Informática (GIDATI), Universidad Pontifici Bolivariana, Circular 1-70-01, Medellín 050031, Colombia Abstract Composite materials have been extensively used on new aircraft airframes because of their advantages over metallic materials. This represents a difficulty for damage detection, a vital task for safety on the aerospace industry, as most nondestructive testing techniques are not effective on these materials since those usually present internal failures like delaminations which are difficult to detect. A miniaturized strain acquisition and wireless transmission system is presented alongside with a novel technique for structural behavior assessment, based on the use of Fiber Bragg Gratings to measure strains and non-supervised classification techniques to recognize different operational conditions. Operational tests were performed on an Unmanned Aerial Vehicles wing’s beam, made of composite materials with the sensors embedded during its manufacturing. Strain measurements were processed using an Optimal Baseline Selection methodology. The tests performed proved the syste ’s capability to identify and separate different operational conditio s for a healthy structure, based on the analysis of its strain fiel s. The implementation of this methodologies can lead to perform real-time damage detection on aerospace complex structures made of composite materials. © 2017 The Authors. Published by Elsevier B.V. Peer-review under responsib lity of the Scientific Committee of ICSI 2017. tr t r l I t rit , I I , - t r , l, ir , rt l techn Alejandro Ca j l t ill a , Joham Alvarez-Montoya a , Juliana Niño-Navia a , t l , b , li i a a rupo de Investigación en Ingeniería eroespacial ( II ), niversidad ontificia olivariana, ircular 1-70-01, edellín 050031, olo bia b rupo de Investigación, esarrollo y plicación en eleco unicaciones e Infor ática ( I I), niversidad ontificia olivariana, ircular 1-70-01, edellín 050031, olo bia str ct site aterials a e ee e te si el se e aircraft airfra es eca se f t eir a a ta es er etallic aterials. is re rese ts a iffic lt f r a a e etecti , a ital tas f r safet t e aer s ac i str , as st estr cti e testi tec i es are t effective on these aterials si ce t se s all rese t i ter al fail res li e ela i ati s ic are iffic lt t etect. i iat rize strai ac isiti a wireless transmission system is presented alongside with a novel technique for str ct ral e a i r assess e t, ase t e se f i er ra rati s t eas re strai s a -s er ise classificati n techniques to recognize iffere t eratio al c itions. perational tests were perf r e a a e erial e icles i ’s ea , a e f c site aterials it the se s rs e e e ri its a fact ri . trai eas re e ts ere processed using an Optimal Baseline Selecti et l . e tests erf r e r e t e s ste ’s ca a ilit t i e tif a se arate iffere t erati al c iti s f r a ealt str ct re, ase t e a al sis f its strai fields. e i le e tati f t is et l ies ca lea t erf r real-ti e a a e etecti aer s ace c le str ct res a e f c site aterials. The A t rs. lis e y Elsevier B.V. eer-re ie er res si ilit f t e cie tific ittee f I I . © 2017 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of ICSI 2017 © 2016 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of PCF 2016. ey ords: structural health onitoring, fiber ragg gratings, un anned aerial vehicles, pattern recognition techniques. Keywords: structural health monitoring, fiber Bragg gratings, unmanned aerial vehicles, pattern recognition techniques. I t r ti l f r

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

* Corresponding author. Tel.: +57-310-487-6758. E-mail address: alejandro.carvajal@upb.edu.co * orresponding author. el.: 57-310-487-6758. - ail address: alejandro.carvajal upb.edu.co

2452-3216 © 2016 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of PCF 2016. 2452-3216  2017 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of ICSI 2017 10.1016/j.prostr.2017.07.163 * Corresponding author. Tel.: +351 218419991. E-mail address: amd@tecnico.ulisboa.pt 2452-3216 © 2017 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of ICSI 2017. 2452-3216 2017 he uthors. ublished by lsevier . . eer-re ie er res si ilit f t e cie tific ittee f I I .