PSI - Issue 2_B

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 Struc ural Integrity 2 (2016) 3593–36 Available online at www.sciencedirect.com ScienceDirect Structural Integrity Procedia 00 (2016) 000–000 Available online at www.sciencedirect.com ScienceDirect Structural Integrity Procedia 00 (2016) 000–000

www.elsevier.com/locate/procedia www.elsevier.com/locate/procedia

www.elsevier.com/locate/procedia

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 Mechanical testi g and n merical predictions of the behavior of braided carbon fiber components Matei-Constantin Miron a *, Harald Katzinger b , Severin Neudorfer a , Emil Pitz a , Zoltan Major a a Institute of Polymer Product Engineeri g, Johannes Kepler University, Altenberger Strasse 69, Linz 4040, Austria b Teufelberger Ges.m.b.H., Vogelweiderstr. 50, Wels 4600, Austria Abstract The current research is presenting three different prediction methods (one analytical and two numerical) implemented to characterize the mechanical behavior of carbon-fiber braided structures. At the end of the paper a comparison between the obtained predictions and the experimentally determined values is being presented. This paper is structured in two parts, the first one presenting the experimental testing of the braided tubular structures as well as flat braided coupons, while the second part is focused on describing the analytical and numerical methods employed. © 2016 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of ECF21. Keywords: braided composites; homogenization; finite element analysis; coupled simulation 1. Int oduction A design tool able to provide fast and reliable prediction of the mechanical properties of braided composite materials depending on the manufacturing processes employed was the aim of the current research. Within the presented content, three different methods of reaching this goal are presented and their predictions are compared with the experimental results. The first described method is purely analytical and relies on computing the stiffness of a representative unit cell (RUC) of the braided material. This method receives as input parameters the geometry and the mechanical properties of the yarn as well as the architecture of the braid used. The RUC elastic constants are 21st European Conference on Fracture, ECF21, 20-24 June 2016, Catania, Italy Mechanical testing and numerical predictions of the behavior of braided carbon fiber components Matei-Constantin Miron a *, Harald Katzinger b , Severin Neudorfer a , Emil Pitz a , Zoltan Major a a Institute of Polymer Product Engineering, Johannes Kepler University, Altenberger Strasse 69, Linz 4040, Austria b Teufelberg r Ges.m.b.H., Vog lweiderstr. 50, Wels 4600, A stria Abstract The current research is presenting three different prediction methods (one analytical and two numerical) implemented to c ara te ize th me anical behavior of carbon-fiber brai ed structures. At the nd of the paper a comparison between the ob ained predi ions and the experim nt lly determined values is being presented. This paper is st uctured in two parts, t first one sen ng the experimental t sting of th braided tub lar tructures as well as flat braid d coupons, while the second part is focused on d scribing the analytic and umerical methods employed. © 2016 The Authors. Publishe by Elsevier B.V. Peer-review under respons bility of the Scientific Committee of ECF21. Keywords: braided composites; homogenization; finite element analysis; coupled simulation 1. Introduction A design tool able to provide fast and reliable prediction of the mechanical properties of braided composite material depending on the manuf cturi g processes empl yed was th aim of the curr nt rese rch. Within th presented content, three different methods of rea hing this goal are presented and their predictions are ompared with th xp rimental results. The first described met od is purely nalytical and relies on computing the stiffness of a repr sentative unit cel (RUC) of the braided material. This method receives as input parameters the geometry and the mechanic l properti s of the yarn as well as he architecture of th braid used. The RUC elastic constants ar Copyright © 2016 The Authors. Published by Elsevier B.V. This is a open ac es ar icle under the CC BY-NC-ND license (http://cre tivec mmons.org/l cens s/by-nc-nd/4.0/). Peer-review und r 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.: +351 218419991. E-mail address: amd@tecnico.ulisboa.pt 2452-3216 © 2016 The Authors. Published by Elsevier B.V. Peer-review un r responsibility of the Scientific Committee of ECF21. 2452-3216 © 2016 The Authors. Published by Elsevier B.V. Peer review under r sponsibility of the Scientific Committee of ECF21. * Corresponding author. Tel.: +43-732-2468-6594; fax: +43-732-2468-6593. E-mail address: matei.miron@jku.at * Corresponding author. Tel.: +43-732-2468-6594; fax: +43-732-2468-6593. E-mail ad ress: matei.miron@jku.at

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.2016.06.448