PSI - Issue 2_A

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) 1375–1382 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 Effect of Microscopic Structure on High-cycle Fatigue Damage in Polycrystalline Nano-copper Takashi Sumigawa a, *, Kenta Matsumoto a , Takayuki Kitamura a a Department of Mechanical Engineering and Science, Kyoto University, Kyoto-daigaku-katsura, Nishikyo-ku, Kyoto 615-8540, Japan Abstract A high-cycle loading method under full load reversal using resonant vibration was developed to investigate the high-cycle fatigue damage of nano-polycrystalline copper in a multi-layered material. A nano-component specimen in which a thin layer of nano polycrystalline copper was sandwiched between a Si substrate and SiN layer was prepared by the focused ion beam technique, and a cyclic load was applied to the specimen. In order to reduce the resonance frequency of the specimen was reduced to less than several hundred kilohertz to control the loading cycle, a gold weight was attached to the specimen tip by tungsten deposition. The high-cycle fatigue loading induced slip bands associated with extrusion/intrusion of approximately several tens of nanometers in width on the upper surface of the Cu layer. The slip band was formed by the microscopic stress field in the grain, which was generated by the deformation constraint between grains. Although the morphology of the extrusion/intrusion was very similar to that observed in fatigue of the bulk material, the size was significantly different. A crack alo g the grain boundary was observed and it seemed to be initiated by the collision of slip bands with the grain boundary. © 2016 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of ECF21. Keywords: Nano-polycrystalline material; high-cycle fatigue; Slip band; Stress field; Resolved shear stress 1. Introduction Metal fatigue often leads to the catastrophic failur of components, and it has thus been widely investigated [Basinski et al. (1980), Basinski et al. (1992), Laird (1986), Mughrabi (1978), Mughrabi (1983)]. Many studies have specifically focused on persistent slip bands (PSBs) [Basinski et al. (1980), Basinski et al. (1992), Laird (1986), Takas a t a r Copyright © 2016 The Authors. ublishe by Elsevier B.V. This is an open access rticl under the CC BY-NC-ND license (http://creativecommons. rg/licenses/by-nc- /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.: +81-75-383-3619; fax: +81-75-383-3619. E-mail address: sumigawa@cyber.kues.kyoto-u.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.2016.06.175