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 Structural Integrity 1 8 66–72 Available online at www.sciencedirect.com ScienceDirect Structural Integrity Procedia 00 (2018) 000 – 000 vailable online at .sciencedirect.co i ir t Structural Integrity Procedia 00 (2018) 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. © 2018 The Authors. P blished 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 Development of new environmentally friendly anticorrosive surface treatments for new Al-Li alloys protection within the frame of Clean Sky2 A. Karanika a, *, N. Vourdas b , A. Makrikostas a , R. Marini a , Th. Plagianakos a , S. Kalogeropoulos a a Hellenic Aerospace Industry S.A. b Technological Educational Institute of Sterea Ellada, Psachna campus, Evia, Greece Abstract Innovative, last generation Al-Li alloys were evaluated in terms of mechanical performance and corrosion protection in order to be used in aircraft structures. Involved alloys are AA2060 and AA2198, where tensile, fatigue, rolling and formability tests were performed and compared against the respective of AA2024. Corrosion protection on the above substrates involves thin film sulphuric acid anodizing or sol-gel technologies. Ab ve aspects are within the technological interests of Hellenic Aerospace Industry that is partici ating in ecoTEC project under Clea Sky 2 pl tform for the even yea s core p oject (2016-2022). 2 The Authors. Published by Elsevier Ltd. This is an open acce s article under th CC BY-NC-ND l cense (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 Gr ek Society of Experime tal Mechanics of Materials Keywords: Al-Li alloys; corrosion protection; mechanical properties; surface treatment 1. Introduction Operational considerations, societal concerns and REACH regulations are creating a growing demand for the devel opment of new effective and environmentally friendly technologies, e.g. Twite et al. (1998) and Dursun, et al. (2014). Aviation industry is responsible for the 2 % of annual global emissions, and reduction of aircraft weight is the main 1 st I ter ati al fere ce f t e ree ciet f eri e tal ec a ics f aterials l t i t ll i l ti i surface treatments for new Al-Li alloys protection it i t l A. Karanika a, *, N. Vourdas b , A. Makrikostas a , . rini a , . l i s a , . l r l s a a Hellenic Aerospace Industry S.A. b Technological Educational Institute of Sterea Ellada, Psachna ca pus, Evia, reece bstract Innovative, last generation l-Li alloys ere evaluated in ter s of echanical perfor ance and corrosion protection in order to be used in aircraft structures. Involved alloys are 2060 and 2198, here tensile, fatigue, rolling and for ability tests ere perfor ed and co pared against the respective of 2024. orrosion protection on the above substrates involves thin fil sulphuric acid anodizing or sol-gel technologies. bove aspects are ithin the technological interests of ellenic erospace Industry that is participating in ecoTE H project under Clean Sky 2 platform for the seven years core project (2016-2022). 2018 The uthors. Published by Elsevier Ltd. This is an open access article under the CC BY-NC-ND license (http://creativeco ons.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 Experi ental echanics of aterials Keywords: l-Li alloys; corrosion protection; echanical properties; surface treat ent 1. Introduction Operational considerations, societal concerns and regulations are creating a gro ing de and for the devel op ent of ne effective and environ ntally friendly technologies, e.g. ite et al. (1998) and ursun, et al. (2014). viation industry is responsible for the 2 of annual global e issions, and reduction of aircraft eight is the ain © 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.: +30 22620 52396 E-mail address: akaranika@haicorp.com Received: May 20, 2018; Received in revised form: July 05, 2018; Accepted: July 16, 2018 * Corresponding author. Tel.: +30 22620 52396 E- ail address: akaranika haicorp.co Received: ay 20, 2018; Received in revised for : July 05, 2018; Accepted: July 16, 2018

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.2018.09.010 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 2452- 3216 2018 The uthors. 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-revie under responsibility of the scientific co ittee of the 1 st International onference of the reek Society of Experi ental echanics of aterials * Corresponding author. Tel.: +351 218419991. E-mail address: amd@tecnico.ulisboa.pt