PSI - Issue 2_B

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ScienceDirect Available online at www.sciencedirect.com Av ilable o line at ww.sciencedire t.com ienceDirect Structural Integrity Procedia 00 (2016) 000 – 000 Procedia Struc ural Integrity 2 (2016) 2575–2582 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 Prediction model for fatigue life considering microstructures of steel Koya Ueda a *, Kazuki Shibanuma a , Masao Kinefuchi b , Yoshiki Nemoto a , Katsuyuki Suzuki c , Manabu Enoki a a Dept. Systems Innovation, Graduate school of Engineering, the University of Tokyo, 7-3-1, Hongo, Bunkyo-ku, Tokyo, Japan b KOBE STEEL,LTD, 1-5-5, Takastukadai, Nishi-ku, Kobe, Hyogo, Japan c Research into Artifacts, Center for Engineering, the University of Tokyo, 5-1-5, Kashiwanoha, Kashiwa-shi, Chiba, Japan Abstract In fatigue life, crack initiation and crack propaga ion is considered separately. Behavior of large crack propagation is explained on the Paris equation. However, there is no model to simul te the behavior from the crack initiation to the large crack propagation. One of this cause is that fatigue life can varies greatly thanks to material microstructures and manufacturing and change of stress. Especially to think the effect of material microstructures is important in materials development. However, there is no model considering quantitative effect of material microstructures. We made prediction model for fatigue life considering material microstructure. This model is for the ferrite-pearlite, most popular steel for th s ructure. Usi g FEM analysis, this model gets stress on the spe imen and divides surface of he test piece into small squares, and fill the squar s with grains using M te Carlo method based on distribution of the grain size. The model gives e ch grains crystal orientation randomly. In each squar s, from the s ress and the crystal orientat on, this model judges the ini iation of th crack on grain. This mode simul es the propagation f small ra k from the crack nucleation. From the stress and the crystal o ientation and the interactio between the slip band and the grain boundary, this model simulates th propagation of th small crack thinking the interaction with grain boundaries. To estimate ex ct fatigue life, this model needs the parameter of the small crack propagation. This parameter is inherent to each materi l. We conducted s m fatigue experiments and bserve propagation of the crack in detail. We conduct d fatigue experiments with anot er distribution grain size to validate our model and we go good agre ment with the xperiments and the model. Katsu

© 2016 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of PCF 2016. © 2016 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of ECF21. l f the Scientific C 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.

Keywords: High Pressure Turbine Blade; Creep; Finite Element Method; 3D Model; Simulation. Keywords: fatigue; microstrucutere; ferrite-pearlite;

* Corresponding author. Tel.: +81-03-5841-6554 E-mail address: ueda@struct.t.u-tokyo.ac.jp

* 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.2016.06.322