PSI - Issue 12

ScienceDirect Available online at www.sciencedirect.com Av ilable o line at www.sciencedire t.com ScienceDirect Structural Integrity Procedia 00 (2016) 000 – 000 Procedia Structu al Integrity 12 (2018) 429–437 Available online at www.sciencedirect.com ScienceDirect Structural Integrity Procedia 00 (2018) 000 – 000 Available online at www.sciencedirect.com 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. © 2018 The Authors. Published by Elsevier B.V. This is an open access article nder the CC BY-NC-ND license (http://creativecommons.org/licenses/by-nc-nd/3.0/) Peer-review under r sponsibility of the Scientific Committee of AIAS 2018 I terna ional Conference on Stress Analysis. AIAS 2018 International Conference on Stress Analysis Analysis of bistable composite laminate with embedded SMA actuators Yogesh Gandhi a, *, A. Pirondi a , L. Collini a a Dipartimento di Ingegneria e Architettura, Università di Parma, Parco Area delle Scienze, 181/A, Parma 43124, Italy Abstract The present work is aimed at the development of a finite element model of a composite laminate, to evaluate the possibility to snap between equilibrium configurations by means of shape memory alloy (SMA) wires. The underlying idea is to p tentially take adva tage of structures which possess multiple equilibrium configurations that can be achieved with a small energy input. Therefore, unsymmetric composite laminates that exhibit bistable response to actuation force are considered. Embedded SMA wires will provide the actuation force by virtue of Shape-Memory Effect i.e. restoring the original shape of a plastically deformed SMA wire by heating it. The Shape Memory Effect is modelled in a simplified way using the Effective Coefficient of Thermal Expansion concept. © 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. Keywords: shape memory alloy cross-ply laminate; snap-through; shape memory effect; bistable structure. 1. Introduction The demanding need for better performance of fixed-wing aircraft, rotorcraft and spacecraft has obviously appeal an interest in adaptive or morphing structural systems which are capable of significant shape change. The bistability behaviour of unsymmetric laminate motivated researchers to exploit this characteristic in numerous aerospace applications. Examples are: i) the use of Morphing Wingtip device whose benefit (in term of induced drag AIAS 2018 International Conference on Stress Analysis Analysis of bistable composite laminate with embedded SMA actuators Yogesh Gandhi a, *, A. Pirondi a , L. Collini a a Dipartimento di Ingegneria e Architettura, Università di Parma, Parco Area delle Scienze, 181/A, Parma 43124, Italy Abstract The present work is aimed at the development of a finite element model of a composite laminate, to evaluate the possibility to snap between equilibrium co figurations by means of shape memory alloy (SMA) wires. The underlying idea is to potentially take advantage of structures which possess multiple equilibrium configurations that can be achieved with a sm ll energy input. Therefore, unsymmetric co posite laminates that exhibit bistable response to actuation force are considered. Embedded SMA wires will provide the actuation force by virtue of Shape-Memory Effect i.e. restoring the original shape of a plastically deformed SMA wire by heating it. The Shape Memory Effect is modelled in a simplified way using the Effective Coefficient of Thermal Expansion concept. © 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 Internatio al Conference on Stress Analysis. Keywords: shape memory alloy cross-ply laminate; snap-through; shape memory effect; bistable structure. 1. In roduction The demanding need for better performance of fixed-wing aircraft, rotorcraft and spacecraft has obviously appeal an interest in adaptive or morphing structural systems which are capable f significant shape change. The bistability behaviour of unsymmetric laminate motivated researc ers to ex loit this characteristic in numerous aerospace applications. Examples are: i) the use of Morphing Wingtip device whose benefit (in term of induced drag © 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.

* Corresponding author. Tel.: +39-320 235 3270. E-mail address: yogesh.gandhi@unipr.it * Corresponding author. Tel.: +39-320 235 3270. E-mail ad ress: yogesh.gandhi@unipr.it

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 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 u der re ponsibility of Scientific ommitt e of AIAS 2018 Internati al 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  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.2018.11.075