PSI - Issue 2_A

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 Struc ural Integrity 2 (2016) 3432–3438 Available online at www.sciencedirect.com Sci nceD rect 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 Formation of nitrided l yer using atmosphe ic-controlle IH-FPP and its effect on the fatigue properties of Ti-6Al-4V alloy under four-point bending S. Kikuchi a, *, S. Ota b , H. Akebono c , M. Omiya b , J. Komotori b , A. Sugeta c , Y. Nakai a a Department of Mechanical Engineering, Kobe University, 1-1 Rokkodai, Nada, Kobe, 657-8501, Japan b D partment of Mecha ical Engineering, Keio University, 3-14-1 Hiyoshi, Kohoku, Yokohama, 223-8522, Japan c Department of Mechanical Science and Engineering, Hiroshima University, 1-4-1 Kagamiyama, Higashihiroshima, 739-8527, Japan Abstract The purpose of this study is to develop a rapid nitriding using a surface modification which is a combination of atmospheric controlled induction-heating fine particle peening (AIH-FPP) and nitrogen gas blow. AIH-FPP was performed for titanium alloy (Ti-6Al-4V ELI grade) at 1173 K for 180 s in a controlled nitrogen atmosphere with an oxygen concentration less than 10 ppm without supplying particles. A nitrogen compound (TiN) was formed on the AIH-FPP treated surface, which results in increasing the surface hard ess of Ti-6Al-4V alloy. To examine the eff ct of AIH-FPP on the fatigue properties of Ti-6Al-4V alloy, four point bending fatigue tests were performed at a stress ratio of 0.1 in air at room tempera ure. It was found that the AIH-FPP treated specim ns showed l w fatigue limit due to the formation of a b ittle compound layer and coarse microstructure. © 2016 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific C mmittee of ECF21. Keywo ds: Surfac modification; Nitriding; In uction heati g; F tigue; Four-point bending; Titanium alloy 1. Introduction Titanium alloy (Ti-6Al-4V) has been widely used in various fields of engineering, such as biomaterials and aerospace components, because this alloy is superior in corrosion resistance and specific strength. In contrast, titanium alloys generally exhibit poorer tribological and wear properties than ferrous materials. Surface modification 21st European Conference on Fracture, ECF21, 20-24 June 2016, Catania, Italy Formation of nitrided layer using atmospheric-controlled IH-FPP and its effect on the fatigue properties of Ti-6Al-4V alloy under four-point bending S. Kikuchi a, *, S. Ota b , H. Akebono c , M. Omiya b , J. Komotori b , A. Sugeta c , Y. Nakai a a Department of Mechanical Engineering, Kobe University, 1-1 Rokkodai, Nada, Kobe, 657-8501, Japan b Department of Mechanical Engineering, Keio University, 3-14- Hiyoshi, Kohoku, Yokohama, 223-8522, Japan c Department of Mechanical S ience nd Engineering, Hiroshima University, 1-4-1 Kagamiyam , Higashihiroshima, 739-8527, Japan Abstract The purpose of this study is to develop a rapid nitriding using a surface modification which is a combination of atmospheric controlled induc ion-heating fine particle peen ng (AIH-FPP) and nit ogen gas blow. AIH-FPP w s performed for titanium alloy (Ti-6A -4V ELI grade) t 1173 K for 180 s i a controlled nitrogen atmosphere with an oxygen concent ation less han 10 ppm without supplyin particles. A nitrogen compound (TiN) was formed on the AIH-FPP treated surface, which result in i creasing the surface hardness of Ti-6 l-4V alloy. To examine the effect of AIH-FPP on the fatigu properties of Ti-6Al-4V alloy, four point bending fatigue tests were perfor ed at stress ratio of 0.1 in air at r om temperature. It was und that the AIH-FPP treated sp cim ns show d lo fatigue li it due to h fo mati n of a brittle compound layer and coarse microstruc ur . © 2016 The Author . Published by Elsevier B.V. Peer-review und r espons bility of the Scientific Committee of ECF21. Keywords: Surface modification; Nitriding; Induction heating; Fatigue; Four-point bending; Tit nium alloy 1. Introduction Titanium alloy (Ti-6Al-4V) has been widely used in various fields of engineering, such as biomaterials and aerospace components, because this alloy s superior i corrosion re istance and specifi strength. In contr st, titanium alloys ge rally exhibit poorer tribological and wear p perties than ferrous materials. Surface modification 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.

* Corresponding author. Tel.: +351 218419991. E-mail address: amd@tecnico.ulisboa.pt 2452-3216 © 2016 The Authors. Published by Elsevier B.V. Peer-review und r responsibil ty 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.: +81-78-803-6329; fax: +81-78-803-6155. E-mail address: kikuchi@mech.kobe-u.ac.jp * Corresponding author. Tel.: +81-78-803-6329; fax: +81-78-803-6155. E-mail address: kikuchi@mech.kobe-u.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.2016.06.428