PSI - Issue 2_B

ScienceDirect Available online at www.sciencedirect.com Av ilable online at www.sciencedirect.com ienceDirect Structural Integrity Procedia 00 (2016) 000 – 000 Procedia Struc ural Integrity 2 (2016) 2375–238 Available online at www.sciencedirect.com ScienceDirect Structural Integrity Procedia 00 (2016) 000–000 ral Integ

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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 Testing and verification modeling of wave-shape formation under explosion welding to laminate AA 2519-Ti6Al4V I. Szachogluchowicz a , L. Sniezek a , H. Sulym b , M. Gloc c * a Faculty of Mechanical Engineering, Military U iversity of Technology, 2 Gen. S Kaliskiego str., Warsaw, 00-908, Poland b Bialystok Technical University, Wiejska Str. 45c, 15-351 Bia ł ystok, Poland c Faculty of Materials Science and Engineering, Warsaw University of Technology, Woloska 141 str, 02-507 Warsaw, Poland Abstract The work describes the process of joining the explosive layered materials. It will be presented attempt analytical process of connecting the wave and its impact on the effects of combining explosive. The calculations will be chosen for the base materials AA2519 and Ti6Al4V. Verification tests will be through the execution and evaluation of metallographic section connections on the scanning microscope. It will be performed confirmatory testing tomography giving the spatial distribution of stresses. Article is complete summary of the results of analytical calculations and attempts to combine the practical effect of explosive laminate AA2519-Ti6Al4V. © 2016 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of ECF21. Keywords: explosion welding,laminate Al Ti, elastodynamics, wave initiation, Rayleigh wave 1. Int oduction Currently, perspective and dynamically developing mainstream is to design composites and laminates including laminate panels. Despite the many advantages of these alloys in progress continuous work on the modification and sometimes contradictory combination of mechanical properties for the commonly used construction materials. Proposal to create a modern material can be layered laminates in which one of the layers is an alloy Ti6Al4V a second stop AA2519. chowicz a z a l c n n ering, Warsaw oloska 141 str, 02-507 Warsaw, Poland process of connecting the wave and its impact on the effects of combining explosiv 2519-Ti6Al4V. n and some t ination of mechani Copyright © 2016 The Authors. Published by Elsevier B.V. This is a open access article under the CC BY-NC-ND license (http://cre tivec mmons.org/licens s/by-nc-nd/4.0/). Peer-review und r responsibility of the Sci ntific 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. E-mail address: ireneusz.szachogluchowicz@wat.edu.pl

* 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.2016.06.297