PSI - Issue 2_B

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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. 21st European Conference on Fracture, ECF21, 20-24 June 2016, Catania, Italy Stage I fatigue cracking in MAR-M 247 superalloy t elevated temperatures Miroslav Šmíd a *, Pavel Hutař a,b , Vít Horník c , Karel Hrbáček d , Ludvík Kunz b a CEITEC IPM, Žižkova 22, Brno, 616 62, Czech Republic b Institute of Physics of Materials, AS CR, Žižkova 22, Brno, 616 62, Czech Republic c Brno University of Technology, Technická 2896/2, Brno 616 69, Czech Republic d PBS Velká Bíteš, a.s., Vlkovská 279, Velká Bíteš, 595 12, Czech Republic Abstract Nickel base superalloys exhibit fatigue fracture behavior with features of brittle-like cleavage cracking under high cycle fatigue loading t temperatures up to approximately 800 °C. This specific fracture behavior was already documented in several studies, but a possible mechanism of fatigue crack propagation under this mode has not been made completely clear yet. The aim of this paper s to put more l ght on the phenomeno by using advanced lectron micr scopy techniques like electron back-scattered diffraction (EBSD) and focused ion beam (FIB) sectioning. Fractured sp cimens f er high cycle fatigue tests were thoroughly examined with the aim to localiz the fatigu crack initiation sit s a d accompanying fe tur s of the fatigue crack propagation. Several specimens we e cross-section d in order to characterize active slip ystems, cy lic plastic d formation localization and fatigue crack propagation. Dislocation structures were studied by transmission electron microscopy (TEM). © 2016 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of ECF21. Keywords: Superalloy; High cycle fatigue; Elevated temperature; MAR-M 247; Fatigue crack initiation 1. Introduction Nickel base superalloys are materials which possess excellent high temperature strength, resistance to oxidation and good creep resistance. They are widely used in electric power generation, aerospace and automotive industry for design and production of various components which are subjected to a combination of high temperature exposure 21st European Conference on Fracture, ECF21, 20-24 June 2016, Catania, Italy Stage I fatigue cracking in MAR-M 247 superalloy at elevated temperatures Miroslav Šmíd a *, Pavel Hutař a,b , Vít Horník c , Karel Hrbáček d , Ludvík Kunz b a CEITEC IPM, Žižkova 22, Brno, 616 62, Czech Republic b Institute of Physics of Materials, AS CR, Žižkova 22, Brno, 616 62, Czech Republic c Brno University of Technology, Technická 2896/2, Brno 616 69, Czech Republic d PBS Velká Bíteš, a.s., Vlkovská 279, Velká Bíteš, 595 12, Czech Republic Abstract Nickel base superalloys exhibit fatigue fracture behavior with features of brittle-like cleavage cracking under high cycle fatigue loading t tem ture up to approximately 800 °C. This specific f acture behav or was already docume t d in several studies, but a possible mechani m of f tigue crack propagation under this mode has not been made completely clear yet. The aim of this paper is to put more light on the phenomen n by using advanced electron microscopy t chniqu s ike lectron back-scattered diffraction (EBSD) and focuse ion bea (FIB) s ctioning. Fractured specimens after high cycle fatigue t sts were thoroughly examined wi h the aim to localize the f tigue crack initiati si es and acco panying featur s f the fatigue crack propagation. Sev ral specime s were cross-sectioned in order to c ar cterize active slip systems, cyclic plastic e ormation localization an fatigue crack propagation. Di loca tructu es were studied by transmi sion l ctron microscopy (TEM). © 2016 The Authors. Published by Elsevier B.V. Peer-review under espons bility of the Scientific Committee of ECF21. Keywords: Superalloy; High cycle fatigue; Elevated temperature; MAR-M 247; Fatigue crack initiation 1. Introduction Nickel base superalloys are materials which possess excellent high temperature strength, resistance to oxidation and go d creep resistance. Th y are widely used in electric power g neration, erospac and automotive industry f r desi n and production of various components which are subjected to a c mbination of high te perature exposure Copyright © 2016 The Authors. Published by Elsevier B.V. This is an open access article under the CC BY-NC-ND license (http://creativecommons.org/licenses/by-nc-nd/4.0/). Peer-review under responsibility of the Scientific Committee of ECF21. © 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.: +420 532 290 362. E-mail address: smid@ipm.cz * Corresponding author. Tel.: +420 532 290 362. E-mail address: smid@ipm.cz

* Corresponding author. Tel.: +351 218419991. E-mail address: amd@tecnico.ulisboa.pt 2452-3216 © 2016 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of ECF21. 2452-3216 © 2016 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of ECF21.

2452-3216 © 2016 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of PCF 2016. Copyright © 2016 The Authors. Published by Elsevier B.V. This is an open access article under the CC BY-NC-ND license ( http://creativecommons.org/licenses/by-nc-nd/4.0/ ). Peer review under responsibility of the Scientific Committee of ECF21. 10.1016/j.prostr.2016.06.378