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 Structu al Integrity 2 (2016) 088– 95 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 Modified Hartman-Schijve fitting of mode I delamination fatigue data and the resulting variation in threshold values G thr Andreas J. Brunner a *, Ahmad Mujtaba b , Steffen Stelzer c , Rhys Jones b a Empa, Swiss Federal Laboratories for Materials Science and Technology, Laboratory for Mechanical Systems Engineering, Überlandstrasse 129, CH-8600 Dübendorf, Switzerland b Centre of Expertise in Structural Mechanics, Department of Mechanical and Aerospace Engineering, Monash University, Victoria 3800, Australia c Institute of Material Science and Testing of Plastics, Montanuniversität Leoben, Otto-Glöckel-Straße 2, A-8700 Leoben, Austria With a view toward applications in structural composite design, mode I (tensile opening) fatigue delamination test data obtained for carbon fiber-reinforced polymer-matrix (CFRP) composites have recently been (re-)analyzed with different fitting approaches for the determination of threshold values G thr . One approach that looks promising as an alternative to the conventional Paris-law type presentation of the data (a double logarithmic plot of delamination length increment per cycle da/dN versus G Imax or  G I ) is a modified Hartman-Schijve fit (also a double logarithmic plot of da/dN, but versus a square-root function of G) requiring four fitting parameters (labelled A,  , D and G thr ). The present paper details a procedure for selecting the fitting para eters A,  , and D in order to d t rmine G thr in a consistent way from the experimental data. For some design approaches, it is important to also hav an estimate of the possible sc tter in experimentally derived values of G thr . The procedure ch sen by the authors yields G thr values an a m asure of the cat er due to experimental variation of the other fit ing parameters. Selected mode I dela ination fatigue data for IM7/8552 CFRP composit s from literature ar use o compare G thr values and their scatter from Paris-law type fitting with those from the modifi d Hartman-S hijve approach. c 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. © 2016 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of ECF21. Abstract

Keywords: High Pressure Turbine Blade; Creep; Finite Element Method; 3D Model; Simulation. Keywords: Polymer-matrix composites; Mode I fatigue testing; Hartman-Schijve fitting analysis; Parametric study

* Corresponding author. Tel.: +41-58-765-4493; fax: (not available). E-mail address: andreas.brunner@empa.ch

* 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.2016.06.012