PSI - Issue 13

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 Structural Integrity 13 (2018) 1421–1426 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. ECF22 - Loading and Environmental effects on Structural Integrity Plasticity and failure behavior modeling of high-strength steels under various strain rates and temperatures: microstructure to components Jun Lian a,b,c, *, We qi Liu a , I anna Papadioti d , Ilias Bella d , Sarath Chandran e , Patrici Verleysen e , Helmut Richter f , Nikolaos Aravas d , Sebastian Münstermann a a Steel Institute, RWTH Aachen University, Intzestraße 1, 52072 Aachen, Germany b Impact and Crashworthiness Lab, Department of Mechanical Engineering, Massachusetts Institute of Technology, Cambridge, MA 02139, USA c Department of Mechanical Engineering, Aalto University, Otakaari 4, 02150 Espoo, Finland d Department of Mechanical Engineering, University of Thessaly, Leoforos Athinon, Pedion Areos, 38334 Volos, Greece e Department of Materials Science and Engineering, Ghent University, Technologiepark Zwijnaarde 903, 9052 Zwijnaarde, Belgium f thyssenkrupp Steel Europe AG, Kaiser-Wilhelm-Straße 100, 47166 Duisburg, Germany Abstract The aim of this study is to establish an integrated material modelling approach, micro, macro and component scales, for investigating the plasticity, damage and fracture behaviour of modern high-strength steels under various strain rates and temperatures. With the established relations between different scales, the approach ultimately provides a knowledge-based and efficient alternative for the damage-tolerant microstructure design to the conventional empirical rules. In this study, we will present the models working at different scales and the scaling strategy between them. For a more general application than quasistatic and room temperature, the models are formul ted with strain rate and temperature depende cy. All mod ls are calibrate by experiments on the corresponding scal and also validated by experiments not involved in the calibration procedure or tests from a higher length scale. As the ulti at goal of the approach is to guide the microstruc ure desig , a fine-resolution digital representatio of the mi ro tructure is target d in study. In addition to the standard phase fraction, grain siz and shape features, fine-tuning of the microstruc ural features, such as texture and misorie tation distribution is also implemented into he synthetic icrostructure model. The impact of these individual microstructure features and their combination on the macroscopic and comp n nt level performance is studied and the optimized microstructure for the desired improvement of the mechanical property can be identified by the proposed approach.

© 2016 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of PCF 2016. © 2018 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the ECF22 organizers. © 2018 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the ECF22 organizers.

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

* Corresponding author. Tel.: +49-241-8092912; fax: +49-241-8095553. E-mail address: junhe.lian@iehk.rwth-aachen.de

* 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 © 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.2018.12.295