PSI - Issue 13

ScienceDirect Available online at www.sciencedirect.com Available online at ww.sciencedire t.com ScienceDirect Structural Integrity Procedia 00 (2016) 000 – 000 Procedia Structu al Integrity 13 (2018) 181–186 Available online at www.sciencedirect.com ScienceDirect Structural Integrity Procedia 00 (2018) 000–000 Available online at www.sciencedirect.com ScienceDirect Structural I t gri y 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. Peer-review under responsibility of the ECF22 organizers. ECF22 - Loading and Environmental effects on Structural Integrity Effect of moisture absorption on the elastic properties in cracked composite laminates with transient hygrothermal conditions M. Khodjet-kesba a *, A. Benkhedda a , E.A. Adda bedia b and B. Boukert a a Laboratoire des sciences aéronautiques, Institut d’aéronautique et des études spatiales,Université de Blida1 b Laboratoire des Matériaux et Hydrologie, Université de Sidi Bel Abbes Abstract A modified Shear-lag model was used to predict the effect of transverse cracks on the elastic properties degradation for [θ m /90 n ] s composite laminates and under different environmental conditions by the variation of temperature and transient moisture concentration distribution in absorption case. Good agreement is obtained by comparing the prediction models and experimental data published by Joffe. Furthermore the cracked angle-ply laminate is submitted to hygrothermal conditions. The transient and non-uniform moisture concentration distribution gives rise to the transient mechanical properties. The obtained results represent well the dependence of the mechanical properties degradation on the cracks density, fibre orientation angle of the outer layers and transie t hygrotherm l conditions. © 2018 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the ECF22 organizers. Keywords: Mechanical properties, Transverse cracking, Tsai model, Shear lag, angle-ply 1. Introduction The evolution f the transverse cracking in composite laminate has been extensively investigated in the literature both experime tally and theoretically. The shear-lag m thod (Berthelot et al. 1996, Tounsi et al. 2006, Adda bedia et al. 2008) and variational approach (Hashin, 1985, Vingradov and Hashin, 2010, Katerelos et al. 2015) are among the most analytical methods used to study the evolution of the transverse cracking in a composite laminate. The modeling ECF22 - Loading and Environmental effects on Structural Integrity Effect of moisture absorption on the elastic properties in cracked composite laminates with transient hygrothermal con itions M. Khodjet-kesba a *, A. Benkhedda a , E.A. Adda bedia b and B. Boukert a a Laboratoire des sciences aéronautiques, Institut d’aéronautique et des études spatiales,Université de Blida1 b Laboratoire des Matériaux e Hydr logie, Université de Sidi Bel Abbes Abstract A modified Shear-lag model was used to predict the effect of transverse cracks on the elastic properties degradation for [θ m /90 n ] s composite laminates and under different environmental conditions by the variation of temperature and transient moisture ncentration distribution in absorption case. Go d agreement is obt ined by comparing the prediction models a d xperimental data published by Joffe. Furthermore the cracked angle-ply laminate is su mitted to hygrothermal c ditions. The transient and non-uniform moisture concentrati n distribution gives rise to the transient echanical properties. The obtained results represent well the dependence of the mechanical properties degradation on the cracks density, fibre ri ntation angle of the outer layers and transient hygrothermal conditions. © 2018 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the ECF22 organizers. Keywords: Mechanical properties, Transverse cracking, Tsai model, Shear lag, angle-ply 1. Introduction The evolution of the transverse cracking in composite laminate has been extensively investigated in the literature both experimentally and theoretically. The shear-lag method (Berthelot et al. 1996, Tounsi et al. 2006, Adda bedia et al. 2008) and variational approach (Hashin, 1985, Vingradov and Hashin, 2010, Katerelos et al. 2015) are among the most analytical methods used to study the evolution of the transverse cracking in a composite laminate. The odeling © 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.: +213662788612; E-mail address: mkhojet@hotmail.fr * Corresponding author. Tel.: +213662788612; E-mail ad ress: mkhojet@hotmail.fr

* Corresponding author. Tel.: +351 218419991. E-mail address: amd@tecnico.ulisboa.pt 2452-3216 © 2018 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the ECF22 organizers. 2452-3216 © 2018 The Authors. Published by Elsevier B.V. Peer review under r sponsibility of the ECF22 organizers.

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. Peer-review under responsibility of the ECF22 organizers. 10.1016/j.prostr.2018.12.030