PSI- Issue 9

ScienceDirect Available online at www.sciencedirect.com Available online at www.sciencedire t.com Scie ceDirect Structural Integrity Procedia 00 (2016) 000 – 000 Procedia Structu al Integrity 9 (2018) 186–198 Available online at www.sciencedirect.com ScienceDirect StructuralIntegrity Procedia 00 (2018) 000–000 Available online at www.sciencedirect.com ScienceDirect StructuralIntegrity 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 f the Gruppo Italiano Frattura (IGF) ExCo. IGF Workshop “Fracture and Structural Integrity” Failure analysis and damage modeling of precipitate strengthened Cu–Ni–Si alloy under fatigu loading Bouchra Saadouki a *, Thaneshan Sapanathan b, c , Philipe Pelca d , Mohamed Elghorba a and Mohamed Rachik b a Laboratoire de contrôle et de caractérisation mécanique des matériaux et des structures (LCCMMS), ENSEM, Casablanca, Morocco b Sorbonne Universités, Université de Technologie de Compiègne, Laboratoire Roberval, CNRS UMR - 7337, Centre de Recherche Royallieu, CS 60319, 60203 Compiègne Cedex, France c Institute of Mechanics, Materials and Civil Engineering, Université catholique de Louvain, B-1348 Louvain-la-Neuve, Belgium d Lebronzealloys – Bornel, 11 rue Méni let, 60540 Bornel, France Abstract Failure analysis and damage evolution in precipitation hardened Cu-2.5Ni-0.6Si alloy are investigated in this study. Firstly, experimental fatigue tests were performed to determine the S-N curve of the material. Then, based on the results of fatigue tests, we have modeled the damage using four linear and cumulative models. The intersection of damage-reliability curves allowed to define three stages of damage during the life cycle for various loading levels. The life fraction β p reveals the stage of slow crack propagation where a preventive action ust be adopted to ensure the proper functioning of the structure. The life fraction βc corresponds to the stage of sudden crack propagation when the damage becomes uncontrollable. © 2018 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Gruppo Italiano Frattura (IGF) ExCo. Keywords: Cu-Ni-Si alloy, fatigue, loading levels, cumulative damage, life fraction. IGF Workshop “Fracture and Structural Integrity” Failure analysis and damage modeling of precipitate strengthened Cu–Ni–Si alloy under fatigue loading Bouchra Saadouki a *, Thaneshan Sapanathan b, c , Philipe Pelca d , Mohamed Elghorba a and Mohamed Rachik b a Laboratoire de contrôle et de caractérisation mécanique des matériaux et des structures (LCCMMS), ENSEM, Casablanca, Morocco b Sorbonne Universités, Université de Technologie de Compiègne, Laboratoire Roberval, CNRS UMR - 7337, Centre de Recherche Royallieu, CS 60319, 60203 Compiègne Cedex, Fr nce c Institut of M chanics, M teri s and Civ l Engineering, Unive sité catholique de Louvain, B-1348 Louvain-la-Neuve Belgium d Lebro z alloys – Bornel, 11 ue M nillet, 60540 Bornel, France Abstract Failure a alysis and damag evolution in precipitation hardened Cu-2.5Ni-0.6Si alloy are investigated in this study. Firstly, experimental fatigue tests were performed to determine the S-N curve of t e material. Then, based on the results of fatigue tests, we have modeled the using four near and cumulative models. The intersection of damag -reliability curves allowed to define three stages f damage during the life cycle for vari us loading levels. The life fracti n β p reveals the stage of slow crack propagation where a preventive action must be adopted to ensure the proper f ctioning of the structure. The life fraction βc corresponds to the stage of sudden crack propagation when the damage becomes uncontrollable. © 2018 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Gruppo Italiano Frattura (IGF) ExCo. Keywords: Cu-Ni-Si alloy, fatigue, loading levels, cumulative damage, life fraction.

© 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.: +212-65-975-0455 E-mail address: bouchra.saadouki@gmail.com * Correspon ing auth r. Tel : +212-65-975-0455 E-mail address: bouchra.saadouki@gmail.com

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 Gruppo Italiano Frattura (IGF) ExCo. 10.1016/j.prostr.2018.06.029 * 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 Gruppo Italiano Frattura (IGF) ExCo. 2452-3216© 2018 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Gruppo Italiano Frattura (IGF) ExCo.