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) 334–341 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 The impact of the multiwall carbon nanotubes on the fatigue properties of adhesive joints of 2024-T3 aluminium alloy subjected to peel Andrzej Kubit a, *, Magdalena Bucior a , Władysław Zieleck i a a Rzeszow University of Technology, Faculty of Mechanical Engineering and Aeronautics, Department of Manufacturing Processes and Production Engineering The paper presents the results of the research undertaken to determine the impact of the epoxy adhesive nanofiller, in the form of multiwall carbon nanotubes (MWCNT), on the fatigue strength and fatigue lifetime of adhesive joints subjected to peel. Carbon nanotubes were synthesized by means of CVD method with Fe-Co catalysts. Upon the completion of the process, the carbon material was subjected to oxidation and to the acid treatment in order to remove amorphous carbon and catalyst particles. The quantity of 1 wt.% of the dried material was added to epoxy adhesives. Such composition went through the process of mixing, ensuring the adequate nanotub s dispe sion. Th prepared composition was used to join two eleme ts made of 2024-T3 aluminium alloy. Adhesive joints underwent high-cycle fatigu peel strength tests with th limit number of cycles of 2 million. The tests were carri d out on t e electr magnetic vibration inductor with the resonance frequency of the flexible adhesive-j ined element of about 600 Hz. For each variant, the fatigue curve and fatigue lifetime were determined for a given level of stress. Thanks to adding carbon nanotubes to epoxy adhesives, the possibility of increasing the fatigue strength by 28.9% and the fatigue lifetime by about 477.2% was discovered. The fatigue strength tests were preceded by static T-peel tests. © 2016 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of ECF21. 0 u y he Scientific Committee of Copyright © 2016 The Authors. Published by El evier B.V. This is an open access le under the CC BY-NC-ND lic nse (http://creativecommons.org/licenses/by-n -nd/4.0/). Peer-review under responsibility of the Scientific Committee of ECF21. Abstract

© 2016 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of PCF 2016. Keywords: carbon nanotubes; fatigue; nanofillers; peel; adhesive joints ubes; fatigue; nanofillers; peel; adhesive joints

Keywords: High Pressure Turbine Blade; Creep; Finite Element Method; 3D Model; Simulation.

* Corresponding author. Tel.: +48 17 8651574. E-mail address: akubit@prz.edu.pl

* Corresponding author. Tel.: +351 218419991. E-mail address: amd@tecnico.ulisboa.pt 2452-3216 © 201 6 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.2016.06.043