PSI - Issue 13

ScienceDirect Available online at www.sciencedirect.com Av ilable o line at www.sciencedire t.com ScienceDirect Structural Integrity Procedia 00 (2016) 000 – 000 Procedia Structu al Integrity 13 (2018) 444–449 Available online at www.sciencedirect.com ScienceDirect Structural Integrity Procedia 00 (2018) 000 – 000 Available online at www.sciencedirect.com ScienceDirect Structural I tegrity Procedia 00 (2018) 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. © 2018 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the ECF22 organizers. ECF22 - Loading and Environmental effects on Structural Integrity Design of Wing Spar Cross Section for Optimum Fatigue Life Khalid Eldwaib a * , Aleksandar Grbović a , Gordana Kastratović b , Mustafa Aldarwish a a Faculty of Mechan cal Engineering, University of Belgrade, Kraljice Marije 16, 11120 Belg ade 35, Ser ia b Faculty of Transport and Traffic Engineering, University of Belgrade, Vojvode Stepe 305 11000 Belgrade, Serbia Abstract Aircraft structur is the most obvious xample where functional requirements d mand light weight and strong structure . Shape and sizing optimization are being increasingly used nowadays f r designing lightweight structural components. The aim of this paper is to present optimization of I-section integral wing spar made of aluminum 2024-T3. The efficient design, based on optimum fatigue life, was achieved using Extended Finite Element Method (XFEM) and its ability to simulate crack growth in complex geometry. The computations were carried out in Morfeo/Crack for Abaqus software which relies on the implementation of XFEM. Shape optimization of the aircraft wing spar beam was conducted by comparing the fatigue crack growth lives for different cross section shapes, but constant cross section area of the spar. The analysis revealed that XFEM is efficient tool for complex three-dimensional configurations optimization where extended fatigue life is one of the most important objectives. © 2018 The Authors. Published by Elsevier B.V. Pe r-review under res on ibili y of the ECF22 organizers. Keywords: aircraft structure; optimization; Extended Finite El ment Method; fatigue life. 1. Introduction The shape optimization is being increasingly used to design lightweight structural components. It is also being used to develop localized shape strategies to restore the operational availability of ageing structural components. However, it is important to note that all new aircraft design and structural changes made to in-service aircraft require a damage tolerance analysis as outlined in the US Joint Services Structural Guidelines JSSG-2006 (1988), which states that all safety-of-flight critical structures should be designed using a damage tolerance analysis. The purpose of this requirement is to ensure that any cracks present in the structure will not cause loss of the structure for some ECF22 - Loading and Environmental effects on Structural Integrity Design of Wing Spar Cross Section for Optimum Fatigue Life Khalid Eldwaib a * , Aleksandar Grbović a , Gordana Kastratović b , Mustafa Aldarwish a a Faculty of Mechanical Engineering, University of Belgrade, Kraljice Marije 16, 11120 Belgrade 35, Serbia b Faculty of Transport and Traffic Engine ring, University of Belg de, Vojvod Stepe 305 11000 B lgrad , Serbia Abstract Aircraft structure is the most obvious example where functional requirements demand light weight and strong structures. Shape and sizing opti ization are being incr asingly used nowadays for designing lightweight structural mponents. The aim f this paper is to resent optimization of I-section int gral ing spar made of aluminum 2024-T3. The efficient design, based on optimum fatigue life, was achieved using Exte ded Finite Element M thod (XFEM) and its ability to simulate crack growth i complex geometry. The computations were carried out in Morfeo/Crack for Abaqus software which relies on the implementatio of XFEM. Shape optimization of the aircraft wing spar beam was conducted by comparing t e fatigue crack growth lives for different cross s ction shapes, but constant cross section area of the spar. The analysis revealed that XFEM is efficient tool f r complex three-dimension l configurations optimization where extended fatigu life is one of th most important objectives. © 2018 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the ECF22 organizers. Keywords: aircraft structure; optimization; Extended Finite Element Method; fatigue life. 1. Introduction The shape optimization is being incre singly used to d sig lightweight structural compon nts. It is also being used to develop localized shape strategies to restore the operational availability of ageing structural components. However, it is important to note that all new aircraft design and structural changes made to in-service aircraft require a damage tolerance analysis as outlined in the US Joint Services Structural Guidelines JSSG-2006 (1988), which states that all safety-of-flight critical structures should be designed using a damage tolerance analysis. The purpose of this requirement is to ensure that any cracks present in the structure will not cause loss of the structure for some © 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: kedwaib@yahoo.com * Corresponding author. E-mail ad ress: kedwaib@yahoo.com

* Corresponding author. Tel.: +351 218419991. E-mail address: amd@tecnico.ulisboa.pt 2452-3216 © 2018 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the ECF22 organizers. 2452-3216 © 2018 The Authors. Published by Elsevier B.V. Peer review under r sponsibility of the ECF22 organizers.

2452-3216 © 2016 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of PCF 2016.

2452-3216  2018 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the ECF22 organizers. 10.1016/j.prostr.2018.12.074