PSI - Issue 5

ScienceDirect Available online at www.sciencedirect.com Av ilable o line at ww.sciencedire t.com ScienceDirect Structural Integrity Procedia 00 (2016) 000 – 000 Procedia Structu al Integrity 5 (2017) 43 –437 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 Probabilistic fatigue crack growth assessment of Al 7075-T6 aerospace component Ahmed Bahloul a *,Amal Ben Ahmed b ,Chokri Bouraoui a a Laboratoire de Mécanique de Sousse, Ecole Nationale d’Ingénieurs de Sousse, Université de Sousse ,BP 264, Cité Erriadh, 4023 Sousse, Tunisie.b b Laboratoire de Mécanique, Matériaux et Procédés, Ecol e Nationale d’Ingénieurs de Sousse, Université de Sousse ,BP 264, Cité Erriadh, 4023 Sousse, Tunisie. Abstract In this paper, an engineering approach of fatigue crack growth mechanism of Al 7075-T6 aerospace component is proposed. The proposed approach was implemented by coupling of Extended Finite Element Method (XFEM), Residual Corrected Stress intensity Factor (RC-SIF) and Monte Carlo simulation (MCS) method. Particular focus was put on considering the effect of material dispersions and the residual stress distribution near the crack tip for evaluating FCG life of cracked attachment lug. Lemaitre- Chaboche’s model has been used to describe material behavior. The iso-probabil stic a-N curves corresponding to5%, 50% and 95% of r liability are determined. The reliability of he proposed engineering approach is verified through a mparison with experimental FCG life data. © 2017 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of ICSI 2017. Keywords: MCS method; Fatigue life prediction, XFEM;RC-SIF; Aerospace component 1. Introduction Fatigue lif is random in nature (Ghonem and Dore (1987)) and deterministic models seem to be unable for predicting FCG life of cracked structures in more efficient and reliable way. Looking for a model /Engineering approach which 2nd International Conference on Structural Integrity, ICSI 2017, 4-7 September 2017, Funchal, Madeira, Portugal Probabilistic fatigue crack growth assessment of Al 7075-T6 aerospace component Ahmed Bahloul a *,Amal Ben Ahmed b ,Chokri Bouraoui a a Laboratoire de Mécanique de Sousse, Ecole Nationale d’Ingénie rs d Sousse, Université de Sousse ,BP 264, Cité Erriadh, 4023 Sousse, Tunisie.b b Laboratoire de Mécanique, Matériaux et Procédés, Ecol e Nationale d’Ingén urs de Sousse, Université de Sousse ,BP 264, Cité Erriadh, 4023 S usse, Tunisie. Abstract In thi paper, an engin ering approach of fatigu crack growth mechanism of Al 7075-T6 aerospac c mponent is proposed. Th propos d approach was implemented by coupling of Extended Finite Element Method (XFEM), Residu l Corrected Str ss intensity Factor (RC-SIF) and Monte C rlo simulation (MCS) method. Par cular foc s was put on considering the effect of material dispersions and the resi ual stress distributi n nea th cr ck tip for e aluating FCG life of cracked attachme t lug. Lemai r - Chab che’s model has been used to d scr be material behavi r. T iso- robabilistic a-N curv s orr sponding to5%, 50% and 95% of r liabil ty are term n . The reliability of th proposed engineering approach is verified throug a comparison wit experimental FCG life data. © 2017 The Autho s. Publ shed by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of ICSI 2017. Keywords: MCS method; Fatigue life prediction, XFEM;RC-SIF; Aerospace component 1. Introduction atigue life is random in nature (Gh nem and Dore (1987)) and deterministic models seem to be unable for predicting FCG life of crack d structur s in mo efficient and reliable way. Looking for a model /Engineering approach which © 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.

* Corresponding author. Tel.: +216-28-062-275. E-mail address: bahloulahmad1@outlook.fr * Correspon ing aut r. Tel.: +216-28-062-275. E-mail address: bahloulahmad1@outlook.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.2017.07.192 * 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.