PSI - Issue 10

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 1 (2018) 264–271 Available online at www.sciencedirect.com ScienceDirect Structural Integrity Procedia 00 (2018) 000 – 000 il l li i i

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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. © 2018 The Authors. Published by Elsevier Ltd. This is an open access article under the CC BY-NC-ND license (http://creativecommons.org/licenses/by-nc-nd/3.0/) Peer-review under responsibility of the scientific committee of the 1st International Conference of the Greek Society of Experimental Mechanics of Materials. 1 st International Conference of the Greek Society of Experimental Mechanics of Materials An experimental evaluation of microdamage in metal matrix composites by means of a SEM-EPMA technique V.N. Kytopoulos a, *, A. Altzoumailis b , J. Venetis a , E. Sideridis a a School of Applied Mathematical and Physical Sciences, Nat. Tech. Univ. Athens, 5 Heroes of Polytechnion Avenue, 157 73 Athens, Greece b School of Chemical Engineering, Nat. Tech. Univ. Athens, 5 Heroes of Polytechnion Avenue, 15773 Athens, Greece Abstract An experimental technique is presented by which mechanical damage in materials can be evaluated. It is based on the Electron Probe Micro-Analysis (EPMA) principle, by which certain analytical possibilities of Scanning Electron Microscopy (SEM) are used. The main scope of the study was to apply this technique for the determination of microcracking damage in edge-cracked metal matrix composites (MMCs). Based on earlier studies this investigation has shown that by this technique the microcracking distribution ahead of an edge-crack under tension can be determined with relatively high reliability. To demonstrate this fact two types of MMCs were investigated. The specimens (shaped s dog-bones with an d e-crack) w re subjected to slow tensile loading up to their ultimate stress. At this stress the loading process was terminated and the EPMA technique was appli d. © 2018 The Aut ors. Published by Elsevier Ltd. This is an open access article under the CC BY-NC-ND license (http://creativecommons.org/licenses/by-nc-nd/3.0/). Peer-review under responsibility of the scientific committee of the 1 st International Conference of the Greek Society of Experimental Mechanics of Materials Keywords: (Micro) damage, x rays; composites; density; edge crack; ductility s of a SEM-EPMA technique p a, , . . . , , , , . . . , , , m © 2018 The Authors. Published by Elsevier Ltd. pen ac e s ar icl BY-NC-ND license (http://creativecommons.or t t ,

1. Introduction

© 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. Modern materials such as aluminum-alloy-based Metal Matrix Composites are the new candidate materials to be used in varieties of engine ring applications. Aluminu and its alloys have been used as main material owing to its wide

* Corresponding author: Tel.: +30 210 7721251; fax: +30 210 7721302. E-mail address: victor@central.ntua.gr Received: May 30, 2018; Received in revised form: July 12, 2018; Accepted: July 20, 2018 . . . .

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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 Ltd. This is an open access article under the CC BY-NC-ND license (http://creativecommons.org/licenses/by-nc-nd/3.0/) Peer-review under responsibility of the scientific committee of the 1st International Conference of the Greek Society of Experimental Mechanics of Materials. 10.1016/j.prostr.2018.09.037 2452- 3216 © 2018 The Authors. Published by Elsevier Ltd. This is an open access article under the CC BY-NC-ND license (http://creativecommons.org/licenses/by-nc-nd/3.0/). Peer-review under responsibility of the scientific committee of the 1 st International Conference of the Greek Society of Experimental Mechanics of Materials i t * Corresponding author. Tel.: +351 218419991. E-mail address: amd@tecnico.ulisboa.pt