PSI - Issue 5

ScienceDirect Available online at www.sciencedirect.com Av ilable o line at ww.sciencedire t.com cienceDirect Structural Integrity Procedia 00 (2016) 000 – 000 Procedia Structu al Integrity 5 (2017) 653–658 Available online at www.sciencedirect.com ScienceDirect Structural Integrity Procedia 00 (2017) 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. 2nd International Conference on Structural Integrity, ICSI 2017, 4-7 September 2017, Funchal, Madeira, Portugal Impact r sponse of polyurethane and polystyrene sandwich panels Oana Mocian, Dan Mihai Constantinescu* , Marin Sandu, Ştefan Sorohan Department of Strength of Materials, University POLITEHNICA of Bucharest, Bucharest 060042, Romania Abstract Sandwich panels with aluminum faces and polyurethane or polystyrene core were tested in impact on an Instron Ceast 9340 impact tower at speeds from 0.77 to 4.5 m/s. The faces were made from Al 6082-T6 sheet with a thickness of 1.5 mm and the thickness of the polyur thane panel (N cu on 100 core of density 100 kg/m 3 ) and of the polystyrene panel (commercial extruded polystyrene core of density 30 kg/m 3 ) were 15 mm, respectively 22 mm. Specimens of 140x140 mm were impacted with a mass of 13.15 kg and the variations of the impact force were monitored during the initial impact at a data acquisition frequency of 200 kHz. The important events took place in less than 15 ms. Particularities of the impact response of the sandwich panels were observed and discussed. The influence of the speed of impact was analyzed for both types of panels. The force variation during impact has a different evolution as influenced by t e core behavior. There are noticed differences in th size and hape of the produced penetration of the skins fter low-velocity impact. © 2017 The Authors. Published by Elsevier B.V. Peer-review und r responsibility of the Scie tific Committee of ICSI 2017. Keywords: sandwich panels; polyurethane and polystyrene cor ; low velocity impact; impact force v riation; damage. Sandwich panels with lightweight structural cores were first used in the aircraft industry in the 1940s to reduce weight and increase flight distance. The heavier conventional sheets were replaced by sandwich structures which became the basic str ctural concept in the aerospac industry since the 1950s. Nowadays, virtually every commercial t ga s, Un of Buchare rest 060042, Romania p kg/m 3 mm 3 . Published by © 2017 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of ICSI 2017 © 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. 1. Introduction

* Corresponding author. Tel.: +40-21-402-9204; fax: +40-21-402-9211. E-mail address: dan.constantinescu@upb.ro

2452-3216 © 2016 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of PCF 2016. 2452-3216  2017 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of ICSI 2017 10.1016/j.prostr.2017.07.035 * Corresponding author. Tel.: +351 218419991. E-mail address: amd@tecnico.ulisboa.pt 2452-3216 © 2017 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of ICSI 2017.