PSI - Issue 14

ScienceDirect Available online at www.sciencedirect.com Av ilable o line at www.sciencedire t.com cienceDirect Structural Integrity Procedia 00 (2016) 000 – 000 Procedia Structu al Integrity 14 (2019) 5 7–513 Available online at www.sciencedirect.com ScienceDirect Structural Integrity Procedia 00 (2018) 000–000 Available online at www.sciencedirect.com ScienceDirect Structural Integrity 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. © 2019 The Authors. Published by Elsevier B.V. This is an open access article under the CC BY-NC-ND license (https://creativecommons.org/licenses/by-nc-nd/4.0/) Selection and peer-review under responsibility of Peer-review under responsibility of the SICE 2018 organizers. 2nd International Conference on Structural Integrity and Exhibition 2018 Study of Polycarbonate Based Nano-composites at High Strain Rate Impact Aisha Ahmed a , Neelanchali Asija a , Hemant Chauhan a , Kartikeya a , Naresh Bhatnagar a * a Mechanical Engineering Department, Indian Institute of Technology Delhi, New Delhi-110016, India Abstract The purpose of this work is to study the applicability f the Polycarbon te (PC)/ Methyl acrylate (MA) blend and their nanocomposites as a matrix based on high strain rate behaviour. The dynamic mechanical experiments have been performed using Split Hopkinson Pressure Bar (SHPB) on all prepared PC/MA blend and their MWCNTs reinforced nano-composites. Toughness at yield has shown a huge improvement after blending of the neat PC. The peak stress increased to 24 % at limiting strain rate of 11514 /s and to 55 % at the limiting strain rate of 13252 /s for the blend and nano-composite, respectively. During high strain rate testing, ductile failure mode can be observed after the toughening of PC, which is suitable for the confinement of ceramic. The blending of MA showed a remarkable improvement in the fracture toughness at high strain rates, which gets further increased in MWCNTs reinforced nanocomposites. © 2018 The Authors. Published by Elsevier B.V. This is an open access article under the CC BY-NC-ND license (https://creativecommons.org/licenses/by-nc-nd/4.0/) Selection and peer-review under responsibility of Peer-review under responsibility of the SICE 2018 organizers. Keywords: Polycarbonate; Methyl acrylate; SHPB; Dynamic Mechanical Testings. 1. Introduction The present-day sophisticated warfare ammunitions urge the need for better energy absorbing, lightweight, multi-hit capable solution for body armours. Therefore, advanced modular composites are the key materials, to trade-off between the energy absorbing capability and wearer mobility, to tackle different threat levels. The higher 2nd International Conference on Structural Integrity and Exhibition 2018 Study of Polycarbonate Based Nano-composites at High Strain Rate Impact Aisha Ahmed a , Neelanchali Asija a , Hemant Chauhan a , Kartikeya a , Naresh Bhatnagar a * a Mechanical Engineering Department, Indian Institute of Technology Delhi, New Delhi-110016, India Abstract The purpose of this work is to study the applicability of the Polycarbonate (PC)/ Methyl ac ylate (MA) l d and th ir na ocomposites as a matrix based on high strain rate behaviour. The dynamic mechanical experiments have been perf rm d using Split Hopkinson Pressure Bar (SHPB) on all prepared PC/MA blend and their MWCNT reinforced nano-composites. Toughness at yield has shown a huge improvement after bl nding of the neat PC. The peak stress increased to 24 % at limit strain r te of 11514 /s and o 55 % at the limiting strain rate o 13252 /s for the blend and nano-composite, espe tively. During high strain rate test , ductile failure mode can e obse ved after the toughening of PC, whic is suit ble for the confinement of ceramic. The blending of MA showed a re arkable improvement in the fracture toughness at high strain rates, which gets further increased in MWCNTs reinforced nanocomposites. © 2018 The Authors. Published by Elsevier B.V. This is an open access article under the CC BY-NC-ND lic nse (https://creat vecommons.org/licenses/by- c-nd/4.0/) Selection and peer-review under responsibility of Peer-review under responsibility of the SICE 2018 organizers. Keywords: Polycarbonate; Methyl acrylate; SHPB; Dynamic Mechanical Testings. 1. Introduction The present-day soph ticated warfare ammunitions urge th need for better energy absorbing, lightweight, multi hit capable solutions for b dy armours. Therefore, advanced modul r composit s are the key materials, to trade-off between the energy absorbing capability and wearer mobility, to tackle different threat levels. The higher © 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.: +91-011-2659-1139. E-mail address: nareshb@mech.iitd.ac.in * Correspon ing author. Tel.: +91-011-2659-1139. E-mail address: nareshb@mech.iitd.ac.in

2452-3216 © 2018 The Authors. Published by Elsevier B.V. This is an open access article under the CC BY-NC-ND license (https://creativecommons.org/licenses/by-nc-nd/4.0/) Selection and peer-review under responsibility of Peer-review under responsibility of the SICE 2018 organizers. 2452-3216 © 2018 The Authors. Published by Elsevier B.V. This is a open access article und r the CC BY-NC-ND lic nse (https://creat vecommons.org/licenses/by- c-nd/4.0/) Selection and peer-review under responsibility of Peer-review under responsibility of the SICE 2018 organizers.

* 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 PCF 2016. 2452-3216  2019 The Authors. Published by Elsevier B.V. This is an open access article under the CC BY-NC-ND license (https://creativecommons.org/licenses/by-nc-nd/4.0/) Selection and peer-review under responsibility of Peer-review under responsibility of the SICE 2018 organizers. 10.1016/j.prostr.2019.05.061