PSI - Issue 13

ScienceDirect Available online at www.sciencedirect.com Av ilable o line at ww.sciencedirect.com ScienceDirect Structural Integrity Procedia 00 (2016) 000 – 000 Procedia Structural Integrity 13 (2018) 2059–2 64 Available online at www.sciencedirect.com ScienceDirect Structural Integrity Procedia 00 (2018) 000–000 Available online at www.sciencedirect.com ScienceDirect Structural Integrity 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 Fracture mechanic and charpy impact properties of a crack in weld metal, HAZ and base metal of welded armor steel Aleksandar Cabrilo a *, Katarina Geric a Faculty of Technical Sciences, Trg Dositeja Obradovica 6, Novi Sad 21000, Serbia Abstract Welding of armored steel is complicated by the high percentage of carbon in the base metal, the presence of faults in the form of cracks and pores that occur in the weld metal and heat affected zone (HAZ) during the welding process. For heavy structural engineering such as military armored vehicles that are frequently under the influence of impact loads, it is important to know the fracture toughness in all zones of the welded joint. The crack formed in base metal or HAZ, due to dynamic or impact loads, can easily continue to propagate to the fusion line, after which its accelerated growth may occur. The fracture mechanics testing was applied to SEN (B) test specimens, which investigated cracks initiation and certain fracture mechanics parameters. Due to the significant interest in quantifying the resistance of material to propagation of cracks, the fracture mechanic was measured in the zone of base metal, weld metal and HAZ, at temperature 20 °C. The fracture toughness in the base metal is 86.1 MPa*m 1/2 , while in HAZ and weld metal zones is 286 MPa*m 1/2 and 355 MPa*m 1/2 , respectively. © 2018 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the ECF22 organizers. Keywords: GMAW welding, Armor steels, Austenitic stainless steel, Fracture mechanics, Instrumented Charpy tests, ECF22 - Loading and Environmental effects on Structural Integrity Fracture mechanic and charpy impact properties of a crack in weld metal, HAZ and base metal of welded armor steel Aleksandar Cabrilo a *, Katarina Geric a Faculty of Technical Sciences, Trg Dositeja Obradovica 6, Novi Sad 21000, Serbia Abstract Welding of armored steel is complicated by the high percentage of carbon in the base metal, the presence of faults in the form of cracks and pores that occur in the wel metal and heat affect d zone (HAZ) during the welding process. For heavy structural engineering such as military armored vehicles that are frequ ntly under the influence of impact loads, it i important to know the fractur toughness in all zones of the welded joint. The crack forme in base metal or HAZ, due to dynamic or impact loads, can easily continue to propagate to the fusion line, after whi h its accelerated growth may occur. The fracture mechanics testing w s applied to SEN (B) test sp cimens, which investigated cracks initiation and certain fract e m ch nics parameters. Due to the significant interest in quantifying the resista c of material to propagation of racks, the fractur mechanic was measured in t zone of base metal, weld metal and HAZ, at temperatur 20 °C. The fracture toughness in the base etal is 86.1 MP *m 1/2 , whil in HAZ and weld metal zones is 286 MPa*m 1/2 and 355 MPa*m 1/2 , respectively. © 2018 The Aut ors. Published by Elsevier B.V. Peer-review under responsibility of the ECF22 organizers. Keywords: GMAW welding, Armor steels, Auste itic stainless steel, Fractu e m chanics, Ins rumen ed Charpy tests, Nomenclature J IC Critical J -integral,

N menclature J IC K IC

Critical J -integral, ritical stress intensity factor,

© 2016 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of PCF 2016. K IC Critical stress intensity factor, R Load ratio, Keywords: High Pressure Turbine Blade; Creep; Finite Element Method; 3D Model; Simulation. Crack length between two successive unloadings Crack length between two successive unloadings Opening displacement R F F a Load ratio, Force value, Force value,

a δ δ

Opening displacement

* 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.2018.12.208