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) 265–272 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 Effect of thickness on behaviour of E-glass/epoxy composite laminates under low velocity impact T Sreekantha Reddy, K Mogulanna, K Gopinadha Reddy, P Rama Subba Reddy*, Vemuri Madhu Armour Division, Defence Metallurgical Research Laboratory, Hyderabad-500 058, India Abstract Fibre-reinforced composite materials have remarkable potential for use in automobile, aerospace and defence applications due to their high specific properties and stiff ess. E- las fiber reinforced c mposite laminates are found to be more promising for various defence applications due to their low cost, easy availability, flexibility in design and processing. In the present study, E glass/epoxy composite laminates were subjected to low velocity impact using 16 mm hemispherical impactor with the impact energy range of 50-150 J. Effect of laminate thickness on impact parameters like peak force, maximum displacement and damage area was experimentally evaluated. It was found that peak force is increased with increase in impact energy up to complete perforation and then became constant. Peak force is found to be increased linearly with the increase in thickness at all impact energies. Maximum displacement has decreased 50% as the thickness of the laminate is doubled. Interaction time/contact duration also decreased due to increased resistance with thickness. Visual inspection of impacted laminates indicates two types of damage regions namely fibre breakage area and delamination area. However, the extent of damage regions and their ratio are found to be thickness dependent. Dominant failure mode gradually changes from fibre breakage to delamination as the thickness is increased. © 2018 The Authors. Published by Elsevi B.V. This is an o n access rticle und the CC BY-NC-ND license (https://crea vecommons.org/lic ns s/by-nc-nd/4 0/) Selection d peer-rev ew under responsibility of Peer-revi w under responsibility of the SICE 2018 organizers. 2nd International Conference on Structural Integrity and Exhibition 2018 Effect of thickness on behaviour of E-glass/epoxy composite laminates under low velocity impact T Sreekantha Reddy, K Mogulanna, K Gopinadha Reddy, P Rama Subba Reddy*, Vemuri Madhu Armour Division, Defence Metallurgical Research Laboratory, Hyderabad-500 058, India Abstract Fibre-reinforced co posite mater als have r markable potent al for use in automobil , erospace and defence application due to the r high specific properties and s iffness. E-glass fiber reinforced composite lam nates are found to be more promising for various defence applications due to th ir low cost, easy a ailability, flexibil ty in design and processing. In the presen study, E glass/epoxy c mposite laminates were subjected to low veloci y impac u ing 16 mm hemispherical im actor wi h the i p ct energy range of 50-150 J. Effect of lamin te thickness on impact parameters like peak forc , maximum displacement and damag area was experim tally evaluated. I was found that peak force is incr ased with increase in impact energy up to complete perforation nd then became co stant. Peak force is found o be ncr a ed linear y with the increase in thickness at all imp energies. Maximum displacement has d cre sed 50% as the thickness of the laminate is oubled. Intera tion ime/contact uration also decreas d due to incre sed resistance with thick ess. Visual inspec ion of impacted l minates indicates two types of damage regions amely fibre breakage rea nd delamination area. However, the extent of damag reg ons a d their ratio are fou d to be thickness dependent. Dominant failure mode gradually changes from fibre breakage to delamination as the thickness is increased. © 2018 The Authors. Published by Elsevier B.V. This is an open access article under the CC BY-NC-ND ic nse (https://creativecommons org/licenses/by- c-nd/4.0/) Selection and peer-review under responsibility of Peer-review under responsibility of the SICE 2018 organizers.

© 2016 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of PCF 2016. Keywords: Composite laminates; Low velocity impact; Peak force; Displacement; Damage area; Keywo ds: Composit laminate ; Low velocity impact; Peak force; Displacement; Damage area;

Keywords: High Pressure Turbine Blade; Creep; Finite Element Method; 3D Model; Simulation.

* Corresponding author. Tel.: +91-40-24588021; fax: +91-40-24588504. E-mail address: rsreddy@dmrl.drdo.in * Correspon ing author. Tel.: +91-40-24588021; fax: +91-40-24588504. E-mail address: rsreddy@dmrl.drdo.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.2019.05.034