PSI - Issue 10

ScienceDirect Available online at www.sciencedirect.com Av ilable o line at ww.sciencedire t.com Sci nceDirect Structural Integrity Procedia 00 (2016) 000 – 000 Procedia Structu al Integrity 1 (2018) 28 –287 Available online at www.sciencedirect.com ScienceDirect 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 Th Authors. P blished by Elsevi r Ltd. This is an open access article under the CC BY-NC-ND lice se (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 LaAlO 3 as overlayer in conventional thermal barrier coatings I. Georgiopoulos a , N. Vourdas b , S. Mirza c , C. Andreouli a , V. Stathopoulos b, * a MIRTEC S.A., Thiva Branch, 72 nd km of Athens-Lamia National Road, 34100, Chalkida, Greece b Technological Education Insttute of Sterea Ellada, Psachna Campus, 34400, Evia, Greece c ELEMENT S.A., Hitchin SG4 0TW, UK Abstract The performance enhancement of Thermal Barrier Coatings (TBC) towards higher service temperatures and longer service life will have a tremendous positive impact on the energy efficiency of turbines for various applications. In this work a study for the evaluation of LaAlO 3 as an overlayer to the YSZ-based TBC is presented. Overlayers on TBC, are desirable in order to add func tionalities, not exhibited by the YSZ, such as CMAS tolerance. However, their effect on the thermal cycling performance of the multi-layered system needs to be examined. NiCrAlY bond-coated nimonic substrates were coated with Yttria Stabilized Zirconia (YSZ) delivered either by Atmospheric Plasma Spraying (APS) or by Suspension Plasma Spraying (SPS). On top of the YSZ layer, a LaAlO 3 overlayer was developed directly from solution feedstock, employing Solution Precursor Plasma Spraying (SPPS). The structure of the LaAlO 3 was c nfirmed by m ans of X-ray diffraction. The effect f the LaAlO 3 ov rl yer on th thermal cycling was evaluated. For all cases the LaAlO 3 improve the performance during thermal cycling at both 1100 o C and 1200 o C. © 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 Keywords: Thermal barrier coatings; LaAlO 3 ; thermal cycling; plasma spraying a b c a b, The performan o e a d t o 0 o t rence of the Greek Society of Experimental Mechanics of Materials Keywords: Thermal barrier coatings; LaAlO ; thermal cycling; lasma spraying

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. Thermal Barrier Coatings (TBCs) are used to insulate and protect the metallic gas turbine engine components from the hot as stream, against high t mperatur corrosion, and subsequent damage. Performance improvement and

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* Corresponding author. Tel.: +30 22280 99688 E-mail address: vasta@teiste.gr Received: May 03, 2018; Received in revised form: July 12, 2018; Accepted: July 20, 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.2018.09.039 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 t * Corresponding author. Tel.: +351 218419991. E-mail address: amd@tecnico.ulisboa.pt