PSI - Issue 5

ScienceDirect Available online at www.sciencedirect.com Av ilable o line at ww.sciencedirect.com ienceDirect Structural Integrity Procedia 00 (2016) 000 – 000 Procedia Structu al Integrity 5 (2017) 347–354 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. 2nd International Conference on Structural Integrity, ICSI 2017, 4-7 September 2017, Funchal, Madeira, Portugal Estimation of the dynamic modal parameters of a small-scaled mockup M. Braz-César a *, J. Ribeiro b , H. Lopes c a Dep. of Applied Mechanics, Polytechnic Institute of Bragança, C. de Santa Apolónia, 5300- 253 Bragança, Portugal b Dep. of Mechanical Technology, Polytechnic Institute of Bragança, C. de Santa Apolónia, 5300- 253 Bragança, Portugal c Dep. of Mechanical Engineering, Polytechnic Institute of Porto, R. Dr. António Bernardino de Almeida, 431, 4200-072 Porto, Portugal This paper presents the experimental and numerical research carried out on a reduced-scaled model to obtain and simulate its dynamic modal properties. A roving impact hammer test was carried out to identify the dynamic modal properties of the structure. The measured input and output values were acquired using a Data Acquisition System (DAQ) in order to compute the corresponding Frequency Response Function (FRF) to characterize its dynamic response. Finally, the experimental results were used to optimize the parameters of a numerical model of the mockup. In this case, the model updating procedure is based on an optimization problem in which a set of parameters representing unc rtainties in the modeling process of the mass, stiffness and damping is optimized to minimize the difference betw en the predicted and measured dynamics of the actual structure. © 2017 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of ICSI 2017. Keywords: Modal analysis; vibrations; model updating This paper is devoted to characteriz the dyna ic properties (frequencies, modal shapes and damping) of an experimental mockup consists on a three-story structure in a shear frame configuration, which can be modeled as a three degrees-of-freedom (DOFs) structure with three lateral displacements representing the vibration of each mass. 2nd International Conference on Structural Integrity, ICSI 2017, 4-7 September 2017, Funchal, Madeira, Portugal Estimation of the dynamic modal param ters of a small-scaled mockup M. Braz-César a *, J. Ribeiro b , H. Lopes c a Dep. of Applied Mecha ics, Polytechnic Institute of Brag nça, C. de Santa Apolónia, 5300- 253 Brag nça, Portugal b Dep. of Mecha ical Technol gy, Polytechn c Institute f Bragança, C. de Sa ta Ap lónia, 5300- 253 Bragança, ugal c Dep. of Mechanical Engineering, Polytechnic Institute of Porto, R. Dr. António Bernardino de Almeida, 431, 4200-072 Porto, Portugal Abstract This paper presents the expe ime tal and nu erical research carried out on a reduc -sc led e to obta n and simulate its dyna ic mo al roperties. A roving impact hammer test was carried out identify the dynamic modal pro er ies of the tructure. The m asured input and ou put values were acqui ed using a Data Acquisition System (DAQ) n order to compute the corres ond ng Fr quency Re ponse Function (FRF) to chara terize its dyn mic r sp nse. Fin lly, the expe imental results were used to optimize the parame rs of a nu rical model of the mockup. In this case, th model updating pro dure s ba d on a o timization problem in which a s t o paramet rs representing uncertainties in the modeling proc ss of the mass, stiffness and dam ing is optimiz d to minimize he difference between the predicted and measured dyna ics of the actual structure. © 2017 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of ICSI 2017. Keywords: Modal analysis; vibrations; model updating 1. Introduction This paper is devoted to characteriz the dynamic properti s ( equencies, modal shapes and da ping) of an exp rimental mockup consists on a three-story struc ur in a shear frame configuration, which can be modeled as a three degrees-of-freedom (DOFs) structure with three lateral displacements representing the vibration of each mass. © 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. Keywords: High Pressure Turbine Blade; Creep; Finite Element Method; 3D Model; Simulation. Abstract 1. Introduction

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.2017.07.181 * Corresponding author. Tel.: +351 218419991. E-mail address: amd@tecnico.ulisboa.pt 2452 3216 © 2017 Th Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of ICSI 2017. 2452-3216 © 2017 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of ICSI 2017. * Correspon ing author. Tel.: +351-273-303070; fax: +351-273-313051. E-mail address: brazcesar@ipb.pt * Corresponding author. Tel.: +351-273-303070; fax: +351-273-313051. E-mail address: brazcesar@ipb.pt