PSI - Issue 2_B

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 Struc ural Integrity 2 (2016) 1951–1958 Available online at www.sciencedirect.com ScienceDirect Structural Integrity Procedia 00 (2016) 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. 21st European Conference on Fracture, ECF21, 20-24 June 2016, Catania, Italy Numerical simulation of plastic strain localization and failure mode transition in metals under dynamic loading Dmitry Bilalov a, *, Mikhail Sokovikov a , Yuri Bayandin a , Vasiliy Chudinov a , Vladimir Oborin a , Oleg Naimark a a Institute of Continuous Media Mechanics of Ural branch of RAS, 1, Ac. Koroleva str., Perm 614013, Russia Abstract The r search is focused on simulation and experimen al investigation of h gh-str in rate l ding t study the mechanism f plastic flow localization and failure mode transition in metals (AlMg6). The task of breaking down barriers by metal shell was examined. Model based on the statistical-thermodynamic description of deformation of solids with mesoscopic defects (microshears and micro-cracks) was used to simulate the behavior of metals under dynamic loading. Experimental studies were also carried out. The real-time lateral surface temperature was measured by high speed infrared camera CEDIP Silver 450M. The consistent result of “in-situ” experiment is the elevated temperature of strain localization area that doesn’t exceed 72°C. The results of numerical simulation are in a good agreement with the in-situ measured infrared experimental data. Experimental and theoretical (numerical) study of dynamic strain localization allowed us to establish the structure induced mechanism of plastic strain localization as possible mechanism of transition to the adiabatic shear failure. Evaluated temperature in the strain localization area (72°C) will not support conventionally used mechanisms of plastic strain localization as autocatalytic temperature control visco-plastic phenomena. Structural study of defect induced scaling properties revealed the correlated behavior of microshear ensemble that can be classified as structural transition providing the dynamic strain localization. © 2016 The Au hors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committe of ECF21. Dmitry Bilalov a, *, Mikhail Sokovikov a , Yuri Bayandin a , Vasiliy Chudinov a Obo a a ric ulatio od agreement with the in-situ measured infrared experimental data. Experimental and po r 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: numerical simulation, dynamic loading, plastic strain localization.

Keywords: High Pressure Turbine Blade; Creep; Finite Element Method; 3D Model; Simulation.

* Corresponding author. Tel.: +7-342-237-8312. E-mail address: ledon@icmm.ru

* 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 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.2016.06.245