PSI- Issue 9

ScienceDirect Available online at www.sciencedirect.com Av ilable o line at ww.sciencedirect.com Sci ceDirect Structural Integrity Procedia 00 (2016) 000 – 000 P o edi Structural Integr ty 9 (2018) 22–28 Available online at www.sciencedirect.com ScienceDirect Structural Int grity Procedia 00 (2018) 000–000 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 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Gruppo Italiano Frattura (IGF) ExCo. IGF Workshop “Fracture and Structural Integrity” Performance characterization of an innovative dual-load controlled tribometer Pierre Leroux a , Duanjie Li a , Davide Morrone b, * a Nanovea Inc., 6 Morgan Ste 156 Irvine, CA 92618, USA b Nanovea Srl, via Balegno 1 10040 Rivalta (TO), Italy Abstract The mainly limitations and problems in test carried out with conventional dead load tribometers are the limits on the loading to a constant load applied by a mass weight and intense uncontrolled vibrations at high loads or high speeds. Nanovea has developed a groundbreaking high load tribometer with an active applied load up to 2000 N and a dual-load control system. In this paper we describe our system and we present the results of the first test carried out and a comparison with the dead load systems giving a clear idea of the improvements granted by the use of a controlled pneumatic load also over the traditional load-controlled techniques. © 2018 The Authors. Publishe by Elsevier B.V. Peer-review under responsibility of the Gruppo Italiano Frattura (IGF) ExCo. Keywords: Load controlled tribometer; Pneumatic load control; Active load tribology test; Nanovea T2000; 1. Introduction Wear takes place in virtually every ind strial sector and imposes costs of ~0.75% of the GDP [1]. Tribology research is vital in improving production efficiency, application performance, as well as conservation of material, energy and the environment. Vibration and oscillation inevitably occurs in a wide range of tribological applications. Excessive external vibration can accelerate the wear process and reduce service performance, and in the end lead to catastrophic failures to the mechanical parts. IGF Workshop “Fracture and Structural Integrity” Performance characterization of an innovative dual-load controlled tribometer Pierre Leroux a , Duanjie Li a , Davide Morrone b, * a N novea Inc., 6 Morgan Ste 156 Irvine, CA 92618, USA b Nanovea Srl, via Balegno 1 10040 Rivalta (TO), Italy Abstract The mainly limitations and problems in test carried out with con entional dead load trib meters are the limits on the loading to constant load applied by a mass weight and i tense uncontrolled vibrations at high loads or high speeds. Nanovea has developed a groundbreaking high load tribometer with an active applied load up to 2000 N and a dual-load control system. In this paper we describe our system and we present the results of th first test carri out and a comparison with t e de load systems giving a clear idea of the improvements granted by the use of a controlled pneumatic load also over the traditional load-controlled techniques. © 2018 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Gruppo Italiano Frattura (IGF) ExCo. Keywords: Load controlled tribometer; Pneumatic load control; Active load tribology test; Nanovea T2000; 1. Introduction Wear takes place in virtually every industrial sector and imposes costs of ~0.75% of the GDP [1]. Tribology research is vital in improving production efficiency, application performance, as well as conservation of material, energy and the environment. Vibration and oscillation inevitably occurs in a wide range of tribological applications. Excessive external vibration can accelerate the wear process and reduce service performance, and in the end lead to catastrophic failures to the mechanical parts. © 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: davide.morrone@nanovea.com * Corresponding author. E-mail address: davide.morrone@nanovea.com

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 B.V. Peer-review under responsibility of the Gruppo Italiano Frattura (IGF) ExCo. 10.1016/j.prostr.2018.06.006 * Corresponding author. Tel.: +351 218419991. E-mail address: amd@tecnico.ulisboa.pt 2452 3216 © 2018 Th Authors. Published by Elsevier B.V. Peer-review under responsibility of the Gruppo Italiano Frattura (IGF) ExCo. 2452-3216 © 2018 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Gruppo Italiano Frattura (IGF) ExCo.