PSI - Issue 2_B

ScienceDirect Available online at www.sciencedirect.com Av ilable o line at ww.sciencedire t.com ScienceDirect Structural Integrity Procedia 00 (2016) 000 – 000 Procedia Structu al Integrity 2 (2016) 182–189 Available online at www.sciencedirect.com ScienceDire t Structural Integrity Procedia 00 (2016) 000 – 000 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 Low cycle fatigue of CFRP laminated composites due to repeated out-of-plane loading Koji Fujimoto a, *, Masahiro Hojo b , Akira Fujita a a School of Engineering, The University of Tokyo, 7-3-1 Hongo, Bunkyo-ku, Tokyo 113-8656, Japan b Institute of Aeronautical Technology, Japan Aerospace Exploration Agency, 7-44-1 Jindaiji-higashi-machi, Chofu-shi, Tokyo 182-8522, Japan Fatigue of CFRP (Carbon Fiber Reinforced Plastics) laminated composites due to repeated out-of-plane loading was investigated using two testing methods. One is the four-point-bending fatigue test using L-shaped specimens and the other is the flatwise tension fatigue test. Interlayer-toughened unidirectional CFRP laminates were used as the specimens. Here, for reduction of the testing time, low ycle fatigue was focused on by setting cyclic loads not to be too small comparing with the static strength of the specimen. Fatigue fracture occurred in a brittle manner with almost no prior deformation in both tests. The fatigue life of the L-shaped specimen was much longer than that of the flatwise tension sp cimen. As th resul s of th fracture surf ce observatio , it uld be seen that the fracture at the CF (Carbon Fiber)/epoxy layer was predominant. However, regions of the toughen d interlayers were also observed on the fracture surface at the curved section of the L-shaped specimen. © 2016 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of ECF21. Keywords: Fatigue; CFRP; Composite material, Out-of-plane loading; Low cycle fatigue; Four-point-bending test; L-shaped specimen; Flatwise tension specimen 21st European Conference on Fracture, ECF21, 20-24 June 2016, Catania, Italy Low cycle fatigue of CFRP laminated composites due to repeated out-of-plane loading Koji Fujimoto a, *, Masahiro Hojo b , Akira Fujita a a School of Engineering, The University of Tokyo, 7-3-1 Hongo, Bunkyo-ku, Tokyo 113-8656, Japan b Institute of Aeronautical Technology, Japan Aerospace Exploration Agency, 7-44-1 Jindaiji-higashi-machi, Chofu-shi, Tokyo 182-8522, Japan Abstract Fatigue of CFRP (Carbon Fiber Reinforced Plastics) laminated composites due to repeated out-of-plane loading was investigated usin tw testing methods. On is the ur-point-bending fatigue test using L-shaped s cimens and the other is the flatwis tension fatigue test. Interlayer-toughened unidirecti al CFRP lam nates were used as the . Here, f r reduction of th t st ng time, low cycle fatigue was focused on by setti g cyclic lo ds not to b too small comparing with th static strength of the specimen. Fatigue fracture occ rred in a brittle manner with alm st no prior def r tion in both tes s. The fatigue life t L-shaped specimen was much longer th n that of the flat ise tensi n specimen. As the results of the fracture surface observation, it could be e n that the fracture at the CF (C rbon Fiber)/epoxy layer was pr dominant. However, reg ons of the toughened interlayers wer also observ d on th fracture surface at the curve ection of the L-shaped specimen. © 2016 The Authors. Published by Elsevi r B.V. Peer-review under espons bility of the Scientific Committee of ECF21. Keywords: Fatigue; CFRP; Composite material, Out-of-plane loading; Low cycle fatigue; Four-point-bending test; L-shaped specimen; Flatwise tension specimen CFRP laminated composites are widely used in the aerospace industries due to high specific strength. With respect to these co posit s, the in-plane strength is important and h s been inv tigated by a great many researchers while less att ntion had been paid to th out-of-plan strength than the in-plane strength. Howev r, the out-of-plan strength or the hrough-thickness streng of these composites has become important because f the incr ase of the pplications 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. CFRP laminated composites are widely used in the aerospace industries due to high specific strength. With respect to these composit , the in-plane strength s important and has been investigated by a great many researchers while less attention had been paid to the out-of-plane strength than the in-plane strength. However, the out-of-plane strength or the through-thickness strength of these composites has become important because of the increase of the applications Abstract 1. Introduction 1. Introduction

* 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 r sponsibility of the Scientific Committee of ECF21. * Corresponding author. Tel.: +81-3-5841-6567; fax: +81-3-5841-6567. E-mail address: tfjmt@mail.ecc.u-tokyo.ac.jp * Corresponding author. Tel.: +81-3-5841-6567; fax: +81-3-5841-6567. E-mail address: tfjmt@mail.ecc.u-tokyo.ac.jp

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.2016.06.024