PSI - Issue 13

ScienceDirect Available online at www.sciencedirect.com Av ilable o line at ww.sciencedire t.com Scie ceDirect Structural Integrity Procedia 00 (2016) 000 – 000 Procedia Structu al Integrity 13 (2018) 686–693 Available online at www.sciencedirect.com ScienceDirect Structural Integrity Procedia 00 (2018) 000 – 000 Available online at www.sciencedirect.com ScienceDirect Structural Int grity 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. ECF22 - Loading and Environmental effects on Structural Integrity Fracture behavior of roll bonded Al-brass-Al multilayer composites – Concept of the maximum undamaged defect size ( d max ) Saeed Mousa 1, *, Amr A. Abd-Elhady 1,2 , Gap-Yong Kim 3 , Hossam El-Din M. Sallam 1,4 † 1 Faculty of Engineering, Jazan University, Jazan 706, Kingdom of Saudi Arabia. 2 Department of Mechanical Design, Mataria, Helwan University, Cairo 11718, Egypt. 3 Department of Mechanical Engineering, ow State University, Ames, IA 50011, USA 4 Department of Materials Engineering, Zagazig University, Zagazig 44519, Egypt. Multilayer sandwich composites consisting of two skin metals and perforated interlayer are rapidly becoming a good substitute for metal structures, especially in the automobile industry. Their good mechanical properties including excellent fatigue and impact strength, as well as damage tolerance, are accomplished. In this study, aluminum-perforated brass-aluminum sandwich composites are fabricated using roll bonding technique. Samples were made at different surface roughness, and their bonding behavior is investigated using peel test. The fracture behavior under mode-I was investigated. The effect of surface roughness (two different sand paper grits 50 and 80) on the fracture energy of mode-I peeling failure is studied experimentally. It is found that, the peeling resistance increased with increasing the surface roughness. To simulate the progressive failure of this sandwich composite, 3-D finite element model is employed in the present work. Virtual-Crack-Closing-Technique (VCCT) debonding model has been adopted to predicate the peeling failure. The conc pt of the maximum size of undamaged defect ( d max ) has been adopted to predict the effect surface roughness on peeling load numerically. The numerical and experimental results showed an agreement between them. Therefore, the present 3D finite element model can be considered as a good candidate to expect the peeling damage in sandwich composites. © 2018 The Au hors. Published by Elsevier B.V. Peer-review under responsibility of the ECF22 organizers. © 2018 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the ECF22 organizers. ECF22 - Loading and Environmental effects on Structural Integrity Fracture behavior of roll bonded Al-brass-Al multilayer composites – Concept of the m ximum undamaged defect size ( max ) Saeed Mousa 1, *, Amr A. Abd-Elhady 1,2 , Gap-Yong Kim 3 , Hossam El-Din M. Sallam 1,4 † 1 Faculty of Engineering, Jazan University, Jazan 706, Kingdom of Saudi Arabia. 2 Dep rtment of Mechanical Design, Mataria, Helwan University, Cairo 11718, Egypt. 3 epartment of Mechanical Engineering, Iowa State University, Ames, IA 50011, USA 4 Department of Materials i eeri , Zagazig University, Zagazig 44519, Egypt. Abstract Multilayer sandwich composites consisting of two skin metals and perforated interlayer are rapidly becoming a good substitute for metal structures, especially in the automobile industry. Their good mechanical prop rties including excellent fatigue and impact strength, as well as damage tolerance, are accomplished. In this study, aluminum-perf rated brass-aluminum sandwich composites re fabricated using roll bonding t ch ique. S mples wer made at different surface roughness, and their bo ding behavior is investigated using p el test. The fracture b havior under mode-I was investigat d. The effect f surface roug ness (two different sand paper grits 50 and 80) on the fracture energy of mode-I peeling failure is studied experimentally. It is found that, the peeling resistance increased with increasing the surfac roughness. To simulate the progressiv failure of this sandwich composite, 3-D finit element model is employed in the present work. Virtual-Crack-Closing-Technique (VCCT) debonding model has been adopted to predicat the peeling failure. The concept of the maxim m size of undamaged defect ( d max ) has been adopte to predict the effect surface roughn ss on peeling load num rically. The numerical and experi ental results sh wed n agre ment between them. Th refore, the pr sent 3 finite element model can be considered as a good candidate to expect the peeling d mage i sandwich composites. © 2018 The Authors. Published by Elsevie B.V. Peer-review under responsibil ty of the ECF22 organizers. Abstract

© 2016 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of PCF 2016. Keywords: Roll bonding; metal/metal multilay r; b ass-aluminum sandwich composites;maximum size of undamaged defect. Keywords: Roll bonding; metal/metal multilayer; brass-aluminum sandwich composites;maximum size of undamaged defect.

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© 2018 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the ECF22 organizers. * Corresponding author. Tel.: +966-5375-55599; fax: +966-17-329-7003. E-mail address: dr.saeed.mousa@gmail.com † Corresponding author. Tel.:+966-5354-80221; fax: +966-17-329-7003. E-mail address: hsallam@jazanu.edu.sa 2452-3216© 2018 The Authors. Published by Elsevier B.V. Peer review under responsibility of the ECF22 organizers. * Corresponding author. Tel.: +966-5375-55599; fax: +966-17-329-7003. E-mail ad ress: dr.saeed.mousa@gmail.com † Correspon ing author. Tel.:+966-5354-80221; fax: +966-17-329-7003. E-mail ad ress: hsallam@jazanu.edu.sa

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.2018.12.114