PSI - Issue 6

ScienceDirect Available online at www.sciencedirect.com Av ilable online at ww.sciencedire t.com ScienceDirect Structural Integrity Procedia 00 (2016) 000 – 000 P o edia Structural Int gr ty 6 7 5–10 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. Copyright © 2017 The Authors. Published by Elsevier B.V. Peer-review und r responsibility of the MCM 2017 organizers. XXVII International Conference “Mathematical and Computer Simulations in Mechanics of Solids and Structures”. Fundamentals of Static and Dynamic Fracture (MCM 2017) Dynamic damage in woven carbon/epoxy composites due to air blast Laurence A. Coles a , Craig Tilton b , Anish Roy c , Arun Shukla d , Vadim V. Silberschmidt e 0F * a Wolfson School of Mechanical and Manufacturing Engineering, Loughborough University, Leicestershire, LE11 3TU, UK b Dept. of Mechanical, Industrial and Systems Engineering, University of Rhode Island, Kingston, RI, 02881, USA Abstract In this study, the dy amic response to air blast observed in a flat plate specim n of 2 x 2 twill weave T300 carbon fibre/epoxy composite is examined, using a combination of non-invasive analysis techniques. The study investigates deformation and damage following air blasts with incident pressures of 0.4 MPa, 0.6 MPa and 0.8 MPa, with wave speeds of between 650 m/s and 950 m/s. Digital image correlation was employed to obtain displacement data from the rear surfaces of the specimens during each experiment, then used to assess the effect of air blast magnitude on the specimen’s response. 3D x-ray tomography was employed to assess the resultant internal damage within the samples, allowing for a damage cloud to be visualized for each specimen. It was demonstrated that the global deformation and transitions in curvature of each specimen appeared to be very similar for all damage cases and that only the out-of-plane displacement increased showing that the pressure magnitude had no effect on the curvature or modes during deformation. Damage was found to propagate from the rear surface of the specimens towards the front surface as the air blast magnitude increased. A finite-element model based on a phenomenological continuum damage approach was also developed and validated against the experimental data. © 2017 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the MCM 2017 organizers. XXVII International Conference “Mathematical and Computer Simulations in echanics of Solids and Structures”. Fundamentals of Static and Dynamic Fracture (MCM 2017) Dynamic damage in woven carbon/epoxy composites due to air blast Laurence A. Coles a , Craig Tilton b , Anish Roy c , Arun Shukla d , Vadim V. Silberschmidt e 0F * a Wolfson School of Me hanical and M ufacturing Engin ering, Loughbor ug University Leicestershire, LE 1 3TU, UK b Dept. of Mechanical, Industrial and Systems Engineering, University of Rhode Island, Kingston, RI, 02881, USA Abstract In this study, the dynamic response to air blast observed in a flat plate specimen of 2 x 2 twill weave T300 carbon fibre/epoxy composite is examined, using a combination of non-invasive analysis techniques. The study investigates deformation and damage following air blasts with incident pressures of 0.4 MPa, 0.6 MPa and 0.8 MPa, with wave speeds of between 650 m/s and 950 m/s. Digital image correlation was employed to obtain displacement data from t rear surfaces of the specimens during e c experiment, then used to assess the effect of air blast magnitude on the specim n’s r sp nse. 3D x-ray tomography w s mpl yed to assess the re ultant internal damage within the sam les, allowing for a damage clo d to be visualized for ch specimen. It was demonstrated th t the glob l deformation and transitions in curvature of eac specimen appeared to be very similar for all damage cases nd that only the out-of-plane displacement increased sh wing th t the pressur magnitude had no ffect on the curvature or modes during deform tion. Damage was found to propagate from the rear surface of the specimens towards the front surface as the air blast magnitude increased. A finite-element model b sed on a phenomenological continuum damage approach was also developed and validated against the experimental data. © 2017 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the MCM 2017 organizers.

© 2016 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of PCF 2016. Keywords: Air blast; CFRP; X-ray tomography; deformation; damage Keywords: Air blast; CFRP; X-ray tomography; deformation; damage

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

* 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 MCM 2017 organizers. 2452-3216 © 2017 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the MCM 2017 organizers. * Correspon ing author. Tel.: +44-(0)-1509-227504; fax: +44-(0)-1509-227502. E-mail address: V.Silberschmidt@lboro.ac.uk * Corresponding author. Tel.: +44-(0)-1509-227504; fax: +44-(0)-1509-227502. E-mail address: V.Silberschmidt@lboro.ac.uk

2452-3216 © 2016 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of PCF 2016.

2452-3216 Copyright  2017 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the MCM 2017 organizers. 10.1016/j.prostr.2017.11.002