PSI - Issue 2_A

ScienceDirect Available online at www.sciencedirect.com Av ilable o line at ww.sciencedire t.com Sci ceDirect Structural Integrity Procedia 00 (2016) 000 – 000 Procedia Structu al Integrity 2 (2016) 69 –696 Available online at www.sciencedirect.com ScienceDirect StructuralIntegrity 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 loss of constraint assessment using σ*- V * approach to describe the effect of crack depth on reference transition temperature T 0 Abhishek Tiwari a,c *, R. N. Singh a,c , Per Ståhle b , J. K. Chakravartty a,c a Mechanical Metallurgy Division, Bhabha Atomic Research Centre, Trombay, Mumbai, India 400085 b Division of Solid Mechanics, Lund University, SE 221 00 Lund, Sweden c HomiBhabha National Institute, Anushaktinagar, Mumbai, India 400094 Abstract The assessment of fracture behaviour of ferritic/ferritic martensitic steels in Ductile to Brittle Transition (DBT) region iscrucial for shallower cracks. In this work the fracture behavior of In-RAFM steels isinvestigated with systematically varying a/W using Master Curve approach. This a/W effect is investigated using σ*- V * approach by calculating the active volume at simulated crack front. It is observed that the fitting parameter of σ*-V* approach is in direct correlation with changing constraint parameter Δ T stress . The constraint effect with v rying crack depth is also c ptured by a n vel constraint parameter referred as Weibull triaxiality. © 2016 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of ECF21. Keywords: Type your keywords here, separated by semicolons ; 1. Introduction The fracture behaviour of ferritic/martensitic steels is being studied for its application as blanket material in fusion reactor. One of the important parameters for the performance assessment of ferritic/martensitic steels is the ductile to brittle t ansition temperatur . n 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.: +91-2559-5304; fax: +91-22-25505151. E-mail address: abhishektiwari@daad-alumni.de

* 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.2016.06.089