PSI - Issue 2_A

ScienceDirect Available online at www.sciencedirect.com Av ilable o line at ww.sciencedire t.com ienceDirect Structural Integrity Procedia 00 (2016) 000 – 000 Procedia Structu al Integrity 2 (2016) 879–886 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 Fatigue and Fracture Resistance of 316H Stainless Steel With Prior Creep Damage Marco Rocchini a *, Catrin M. Davies a , David W. Dean b , Kamran M. Nikbin a a Mechanical Engineering Deparment, Imperial College London, South Kensington Campus, London SW7 2AZ, UK b EDF Energy, Barnett Bay, Barnwood, Gloucester GL4 3RS, UK Abstract 316H stainless steel is widely used in high temperature components for advanced gas cooled reactors. Some plats have been de-rated to temperatures below the creep regime, due to the presence of creep damage in some components. However, such damaged or defected components must still satisfy structural integrity criteria for fatigue crack growth and fracture toughness behaviour. Therefore work has been performed to examine the fatigue and fracture toughness resistance of prior creep damaged material. A large block of material has been globally creep damaged (GCD) at 550 °C to the onset of tertiary creep behaviour. In this work, half sized compact tension C(T) specimens have been extracted from 316H blocks which were both pre-compressed and prior creep damaged at 550 °C. Fatigue crack growth and fracture toughness tests were subsequently performed on them. Note that prior to creep, this block was pre-compressed (PC) to 8% plastic strain at room temperature in order to work harden the material and limit the influence of crack tip plasticity in subsequent creep crack growth tests. The results, when compared to those previously obtained from as-received (AR), pre-compressed (PC) and locally creep damaged (LCD) standard sized C(T) s mpl s, show a verall reduction of the fracture energy J . However, the global creep damage method does not troduce substan ia c anges on the fatigue crack growth b aviour of the material. © 2016 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of ECF21. M i a ea b in a 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: 316H; Fatigue Crack Growth; Fracture Toughness; Creep Damage, Pre-Strain

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

* Corresponding author. Tel: +44(0)2075947035 E-mail address: marco.rocchini14@imperial.ac.uk (M. Rocchini)

* Corresponding author. Tel.: +351 218419991. E-mail address: amd@tecnico.ulisboa.pt 2452-3216 © 2016 The Authors. Published by Elsevier B.V. Peer-revi w 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.2016.06.113