PSI - Issue 2_A

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 Structu al Integrity 2 (2016) 08 – 87 Available online at www.sciencedirect.com Structural Integrity Procedia 00 (2016) 000–000 Available online at www.sciencedirect.com Structural Integrity Procedia 00 (2016) 000–000 Available online at www.sciencedirect.com 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 Characterising resistance to fatigue crack growth in adhesive bonds by measuring release of strain energy J.A. Pascoe a, ∗ , R.C. Alderliesten a , R. Benedictus a a Structural Integrity & Composites, Faculty of Aerospace Engineering, Delft University of Technology, 2629 HS Delft, The Netherlands Abstract Measurement of the energy dissipation during fatigue crack growth is used as a technique to gain more insight into the physics of the crack growth process. It is shown that the amount of energy dissipation required per unit of crack growth is determined by G max , whereas the total amount of energy available for crack g owth in a single cycle is determined by ∆ √ G 2 . c 2016 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of ECF21. Keywords: Adhesive Bonds; Fatigue Crack Growth; Strain Energy Dissipation Nomenclature 21st European Conference on Fracture, ECF21, 20-24 June 2016, Catania, Italy Characterising resista ce to fatigue crack growth in adhesive bonds by measuring release of strain energy J.A. Pascoe a, ∗ , R.C. Alderliesten a , R. Benedictus a a Structural Integrity & Composites, Faculty of Aerospace En ineering, Delft U iversity of Technology, 2629 HS Delft, The Netherlands Abstract Measurement of the energy dissipation during fatigue crack growth is used as a technique to gain more insight into the physics of the crack growth process. It is shown that the amount of energy dissipation required per unit of crack growth is determined by G max , wh reas the total amoun of energy available for crack growth in a single cycle is determined by ∆ √ G 2 . c 2016 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of ECF21. Keywords: Adhesive Bonds; Fatigue Crack Growth; Strain Energy Dissipation 21st European Conference on Fracture, ECF21, 20-24 June 2016, Catania, Italy Characterising resistance to fatigue crack growth in adhesive bonds by easuring release of strain energy J.A. Pascoe a, ∗ , R.C. Alderliesten a , R. Benedictus a a Structural Integrity & Composites, F culty of Aerospace Engineering, Delft University of Technology, 2629 HS Delft, The Netherlands Abstract Measurement of the energy dissipatio during fatigue crack growth is used as a technique to gain m re nsight into the physics of the crack growth process. It is shown that the amount of energy dissipation required per unit of crack growth is determined by G max , whereas the total amount of energy available f r crack growth in a single cycle is determined by ∆ √ G 2 . c 2016 The Autho s. Publish d by E sevier B.V. Peer-review under responsibility of the Scientific Committee of ECF21. Keywords: Adhesive Bonds; Fatigue Crack Growth; Strain Energy Dissipation Nom nclature 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/). r iew under esponsibility of the Scientific Committee of ECF21.

Nomenclature

a a A C a A C A C d G d

Crack length Crack length

n n

Calibration parameter Calibration parameter Calibration parameter

© 2016 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of PCF 2016. Fit parameter in the Jones model Curve fit parameter P Force R Load ratio rack length n Fit parameter in the Jones model P Force

Displacement Fit parameter in the Jones model Curve fit parameter

U w P U w R U w

Strain energy Force Load ratio Strain energy

Displacement

Keywords: High Pressure Turbine Blade; Creep; Finite Element Method; 3D Model; Simulation. Curve fit parameter R Load ratio

G Strain energy release rat G th Threshold strain energy release rate K Stress intensity factor N Cycle number n Curve fit parameter d Displacement G train energy release rate G th Threshold strain energy release rate K Stress intensity factor N Cycle number n Curve fit parameter Strain energy release rate th Threshold strain energy release rate K Stress intensity factor N Cycle number n urve fit parameter

Width ∆ G Strain energy release rate range ∆ K Stress intensity factor range γ Mean stress sensitivity train energy Width ∆ G Strain energy release rate range ∆ K Stress intensity factor range γ Mean stress sensitivity Width ∆ G Strain energy release rate range ∆ K Stress intensity factor range γ Mean stress sensitivity

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.2016.06.011 ∗ Corresponding author. Tel.: + 31-15-2786604 ; fax: + 31-15-2781151. E-mail address: j.a.pascoe@tudelft.nl; johnalan.pascoe@gmail.com 2452-3 16 c 2016 The Authors. Published by Elsevi r B.V. Peer-review under responsibility of the Scientific Comm ttee f ECF21. ∗ Corresponding author. Tel.: + 31-15-2786604 ; fax: + 31-15-2781151. E-mail address: j.a.pascoe@tudelft.nl; johnalan.pascoe@gmail.com 2452-3216 c 2016 The Auth rs. Publi hed by Elsevier B.V. e r-review under responsibil ty of the Scientific Committee of ECF21. ∗ Corresponding author. Tel.: + 31-15-2786604 ; fax: + 31-15-2781151. E-mail address: j.a.pascoe@tudelft.nl; johnalan.pascoe@gmail.com 2452-3216 c 2016 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of ECF21. * Corresponding author. Tel.: +351 218419991. E-mail address: amd@tecnico.ulisboa.pt