PSI - Issue 2_A

ScienceDirect Available online at www.sciencedirect.com Av ilable o line at ww.sciencedire t.com cienceDirect Structural Integrity Procedia 00 (2016) 000 – 000 Procedia Struc ural Integrity 2 (2016) 2447–2455 Available online at www.sciencedirect.com ScienceDirect Structural Integrity Procedia 00 (2016) 000–000 Available online at www.sciencedirect.com Sci nceDirect 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 A Probabilistic Fatigue Assessment Diagram To Get A Guaranteed Lifetime With A Low Probability Of Failure S. Jallouf, a G. Pluvinage, b K. Casavola, a and C. Pappalettere a * a Politecnico di Bari Bari (Italy) b FM.C Silly-sur-Nied 57530 (France) Abstract In order to guarantee a fatigue lifetime with a conventional and low probability of failure, a probabilistic fatigue assessment diagram is proposed as a tool. The safe domain is lim ted by he fatigue failure assessment curve, which depends on material properties through Basquin’s exponent, endurance limit and low cycle fatigue domain . From the double-truncated distribution of the targeted maximum applied stress, it is possible to find the failure probability and its associated safety factor. An example of an aeronautical component made of TA6V titanium alloy welded by laser and exhibiting an undercut at the weld toe is given. © 2016 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of ECF21. 1. Introduction The Failure Assessment Diagram (FAD) is a tool for failure analysis and is part of several standards and norms [SINTAP (1999)]. In the deterministic case, the results are in the form of failure or no failure. However, the FAD was originally designed for deterministic input information, while realistic assumptions require the consideration of uncertainties. Therefore, the fracture mechanics approach is associated with Monte Carlo [Pluvinage and Schmitt (2014)] simulation, which takes into account the uncertainties of statistical distributions. The result of such an analysis is a quantitative assessment in terms of probability of failure. In the FAD, a defect in a structure submitted to loading is represented by an assessment point with coordinates, the non-dimensional load and the non-dimensional crack driving force. The position of this ass ssment point that is behind or below the failure assessment curve defines the 21st European Conference on Fracture, ECF21, 20-24 June 2016, Catania, Italy A Probabilistic Fatigue Assessment Diagram To Get A Guaranteed Lifetime With A Low Probability Of Failure S. Jallouf, a G. Pluvinage, b K. Casavola, a and C. Pappalettere a * a Politecnico di Bari Bari (Italy) b FM.C Silly-sur-Nied 57530 (France) Abstract In order to guar ntee a fatigue lifetime with a conventional and low probability of failure, a prob bilistic fatigue assessment diagram is proposed as a tool. The safe domain is limited by the fatigue failure assessment curve, which depends on material properties through Basquin’s exponent, endurance limit and low cycle fatigue domain . From the double-truncated distribution of the targeted maximum applied stress, it is possible t find the failure probability and its associated safety factor. An example of an aeronautical component made of TA6V titanium alloy welded by laser and exhibiting an undercut at the weld toe is given. © 2016 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of ECF21. 1. Introduction The Failure Assessment Diagram (FAD) is a tool for failure analysis and is part o sev ral standards and norm [SINTAP (1999)]. In the d t rmi isti case, the results are in th form of failure or no failure. How ver, the FAD was origin lly design d for det rministic input informati n, while realistic assumptions require the consideration of uncertainties. Therefore, the fracture mechanics approach is as ociated w th Monte Carlo [Pluvinage and Schmitt (2014)] simulation, which takes into accou t the uncertainti s of statistical distributions. The result of such an an lysis a quantitative assessm nt in terms of probability of failure. I the FAD, a defect in structure sub itted to loading is r present d by an assessment point with co rdi ates, the non- im nsional load and the non-dimensional crack driving force. The position of this assessment point that is behind or below the failure assessment curve defines the 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. E-mail address: pluvinage@cegetel.net * Corresponding author. E-mail address: pluvinage@cegetel.net

* 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 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.2016.06.306