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) 197–204 Available online at www.sciencedirect.com ScienceDire t Structural Integrity Procedia 00 (2016) 000–000 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 The influenc of friction on delamination in Fibre-Reinforced Composites, An SGBEM implementation. Jozef Kšiňan*, Roman Vodička Technical University of Košice, Civil Engineering Faculty, Vysokoškolská 4, 042 00 Košice, Slovakia Abstract A new cohesive contact model coupling the interfacial damage and the Coulomb friction is presented from the mathematical and engineering points of view. The formulation of the Cohesive Interface Model (CIM) predicts the interface damage assuming the frictional contact between debonded surfaces. The contribution discusses the role, influence and the intensity of the friction in the proce s of he interface debonding in two subsequent fracture effects: the crack initiation and the crack propagation. A concept of an energy-based formulation is applied to model the process of interface debonding. The numerical solution is approximated by a time stepping pr cedure and it has been impl ment d in the Symmetric Galerkin Bou dary Element Method code. The developed contact model has been appli d in Fibre-Reinforced Composite (FRC) nd the achieved results prove the impact of the friction on the debonding process in FRC. © 2016 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of ECF21. Keywords: Interface danage; Cohesive model; Coulomb friction; Symmetric Galerkin BEM; Quasi-static delamination. 1. Interface contact model The actual trends in development of composite materials, proves that the analysis of the fibre-matrix debonding process is one of the crucial aspects in prediction of delamination in the fibre-reinforced composites. One of the most efficient ways for the n merical mod lling of the interface damage, espec ally the crack onset and growth, is by applying of the contact models at the fibre-matrix interface. The problem of the interface debonding of the single inclusion has been studied in detail in the works of Mantič (2009), Mantič and García (2012) and Correa et al. (2008). 21st European Conference on Fracture, ECF21, 20-24 June 2016, Catania, Italy The influence of friction on delamination in Fibre-Reinforced Composites, An SGBEM implementation. Jozef Kšiňan*, Roman Vodička Technical University of Košice, Civil Engineering Faculty, Vysokoškolská 4, 042 00 Košice, Slovakia Abstract A new cohesive contact model coupling the interfacial damage and the Coulomb friction is presented from the mathematical and engineering points of view. The formulation of the Cohesive Interfac M del (CIM) predicts th interface damage assuming the frictional contact betwe n debonded s rfaces. The contribution discusses the role, influence and the intensity of th friction in process of the in erfac debondi g in two subsequent fract re effects: the crack initiation and the crack propagation. A concept of an energy-based formulation is applied t mod l the pro ess of interface debonding. The numerical soluti n is approximated by a tim stepping procedure and it has b en implement d in the Symm tri Galerkin Boundary El ment Meth d code. The developed contact model has been applied in Fibre-Reinforced C posite (FRC) and the achieve results prove the impact of t fri tion on the debonding process in FRC. © 2016 The Authors. Published by Elsevier B.V. Peer-review under esponsibility of th Scientific Committee of ECF21. Keywords: Interface danage; Cohesive model; Coulomb friction; Symmetric Galerkin BEM; Quasi-static delami ation. 1. Interface contact model The actual trends in development of composite materials, proves that the analysis of the fibre-matrix debonding process is one of the crucial aspects in predicti n of delamination in the fibr -reinforced composit s. One of the most effi ient ways for the numerical modelling of the interface damage, especially the crack on e and gr w , is by appl i g of the contact models at the fibre-matrix n . The problem of the inte f e debonding of the s ngle inclusion has b en s udied in det il in the works of Mantič (2009), Mantič and García (2012) and Correa et al. (2008). 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: jozef.ksinan@tuke.sk * Corresponding author. E-mail address: jozef.ksinan@tuke.sk

* 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.2016.06.026