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 Struc ural Integrity 2 (2016) 2764–2771 Available online at www.sciencedirect.com ScienceDirect Structural Integrity Procedia 00 (2016) 000–000

www.elsevier.com/locate/procedia

www.elsevier.com/locate/procedia

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 Structural and physical criteria of ultimate state of material before fracture M.R. Tyutin a *, L.R. Botvina a , V.P. Levin a , T.B. Petersen b , Yu.A. Demina a , A.P. Soldatenkov a , A.I. Demin c a A.A. Baikov Institute of Metallurgy and Materials Science, Russian Academy of Sciences,49 L ninskiy prospect, Moscow, 119334, Russia b Diapac ltd, Gabrichevskogo 5, Moscow, 125367, Russia c OJSC “Orgenergogaz”, Luganskaya 11, Moscow, 115304, Russia Abstract The size of plastic zone and parameters characterizing damage within the zone are estimated by the methods of replicas, acoustic emission, metal magnetic memory, ultrasonic attenuation and finite elements analysis. The relation between the estimated physical parameters on the one hand and the plastic zone size and the characteristics of real damage in this zone, on the other, is established. © 2016 The Authors. Published by Elsevier B.V. Peer-review under res onsibility of the Scientific Committee of ECF21. Keywords: Damage, plastic zone, strength, fracture, acoustic emission, ultarsonic attenuation, metal magnetic memory, von Mises equivalent strain 1. Introduction Evaluation of damage and residual life of structural elements by nondestructive methods is complicated by the absence of stable c rrelations between characteristics of the actual damage of the material at various stages of loading and the physical propertie estimated by acoustic, agn tic and other non-destructive techniques. Most of studies only devoted to the analysis of the relationship between these properties, the loading parameters and mechanical properties (Shiotani et al., 2003, Carpinteri et al. 2009, Gorkunov et al. 2004, 2014). ure 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. © 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.: +7-499-135-9683; fax: +7-499-135-8680. E-mail address: tyutin@imet.ac.ru

* Corresponding author. Tel.: +351 218419991. E-mail address: amd@tecnico.ulisboa.pt 2452-3216 © 2016 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.2016.06.345