PSI - Issue 5

ScienceDirect Available online at www.sciencedirect.com Av ilable o line at ww.sciencedire t.com cienceDirect Structural Integrity Procedia 00 (2016) 000 – 000 Procedia Structu al Integrity 5 (2017) 271–278 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 Moisture absorption effect on the stress distribution of the cross-ply laminates with transverse matrix cracks Khodjet-Kesba Mohamed a* , Benkhedda Amina a , Adda Bedia b , Boukert billel a a Laboratoire des sciences aéronautiques, Institut d’aéronautique et des études spatiales, Université de Blida 1, Algérie b Laboratoire matériaux et hydrologie, Université Sidi Belabes, Algérie The purpose of this paper is to investigate the moisture absorption effect on the stress distribution of the cross-ply laminates with transverse matrix cracks. Two analytical models were used to evaluate the stress distribution, Shear Lag and the variational approach. The results show that a complete parabolic variation of displacement gives a good approximation of the stress distribution compared o the finite element analysis. Furthermore, the cracked cross ply laminate is submitted different temperature and moisture concentration distribution. The predicted model shows that moisture absorption has a significant effect on the stress distribution specially at the higher cra k density. © 2017 The Authors. Published by Elsevier B.V. Peer-review under responsibility of th Scientific Committee of ICSI 2017. Keywords: Transverse cracking, Longitudinal stress, Hygrothermal effect, Cross ply laminates; Moisture absorption 1. Introduction The evolution f the transverse cracking in the 90° layers was characterized in 1977 by Reifsnider (1977) and Garrett and Bailey (1977) for cr ss-ply laminates loaded in the 0° ply direction by static or fatigue traction test. Then developed in many analyses in the literature (Boniface and Ogin 1989, Groves et al. 1987) where they provide a means of evaluating t e different hypotheses of the approaches an their consequences on the material properties of cracked laminates. 2nd International Conference on Structural Integrity, ICSI 2017, 4-7 September 2017, Funchal, Madeira, Portugal Moisture absorption effect on the stress distribution of the cross-ply laminates with transverse matrix cracks Khodjet-Kesba Mohamed a* , Benkhedda Ami a a , Adda B dia b , Boukert billel a a Laboratoire des sciences éronautiques, Institut d’aé onautique et des tudes spatiales, Univ rsité de Blida 1, Algérie b Laboratoire matériaux et hydrologie, Université Sidi Belabes, Algérie Abstract The pu pose of this paper is to investigate the moisture ab orpti n effec on the stre s distribution of the cross-ply lamin tes with transverse mat ix cracks. Two analytical models were used to evaluate the str s distribution, Shear Lag and the variational appro ch. The r sults show that a complete parabolic variation of displacement gives a good approx mation of the s ress dis ribution compa d to the finite element a alysis. Furthermore, the cracked cross ply l minate is submitted different temperature and moisture concentr tion distribution. The pred cted m del shows that moisture absorption has a significant eff ct on the stress distribution espec ally at the higher crack density. © 2017 The Autho s. Publ shed by Elsevier B.V. Peer-review und r responsibility of the Scie tific Committee of ICSI 2017. Keywords: Transverse cracking, Longitudinal stress, Hygrothermal effect, Cross ply laminates; Moisture absorption 1. Introduction The evolution of the transverse cracking in the 90° layers was chara terized in 1977 by Reifsnider (1977) and Garrett and Bailey (1977) for cross-ply laminates loaded in the 0° ply direction by static or fatigue traction t st. Then dev loped in many analyses in the literature (Bonif ce and Ogin 1989, Groves et al. 1987) where they provide a means of evaluating the different hypotheses of the approaches and their consequences on the material properties of cracked laminates. © 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

* Corresponding author E-mail address: mkhojet@hotmail.fr * Corresponding author E-mail address: mkhojet@hotmail.fr

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.2017.07.131 * 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.