PSI - Issue 14

ScienceDirect Available online at www.sciencedirect.com Av ilable o line at www.sciencedire t.com Sci ceDirect Structural Integrity Procedia 00 (2016) 000 – 000 Procedia Structu al Integrity 14 (2019) 676–683 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

www.elsevier.com/locate/procedia www.elsevier.com/locate/procedia

www.elsevier.com/locate/procedia

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 Role of laminate fracture energy on ballistic performance of glass composite laminates P Rama Subba Reddy a * , T Sreekantha Reddy a , K Mogulanna a , G Seshagiri Rao a , Vemuri Madhu a , K Venkateswara Rao b a Armour Division, Defence Metallurgical Research Laboratory, Hyderabad-58, India b Jawaharlal Nehru Technological University, Hyderabad – 72, India Abstract In the present study varying t ickness of (5-25mm) E-glass composite laminates have been prepared through hot compression moulding method using different matrix systems such as phenolic and epoxy with E-glass fiber as a common reinforcement. The laminates were initially evaluated for their mechanical and mode-I inter laminar fracture energy as per ASTM test methods. It is observed that the laminate having epoxy matrix has shown higher mechanical and fracture energy than the laminate made using phenolic matrix. This is due to the strong adhesion bond between the epoxy matrix and glass fiber reinforcement. Further, the laminates were subjected to ballistic impact tests against 7.62X 39 mild steel projectiles. It is observed that the laminate having lower fr cture energy (E-glass/phenolic) has shown better energy absorption under ballistic impact. Failur analysis on post impacted laminates have been studied using C-scan analysis and observed that E-glass/epoxy composite laminate has shown limited damage rea, whereas E-glass/phenolic composite laminate has shown more damage area. This study rev als th t the laminate having lower fracture energy for delamination is more suitable for higher energy absorption due to dissipation of energy in lateral directions under ballistic impact conditions. © 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. 2nd International Conference on Structural Integrity and Exhibition 2018 Role of laminate fracture energy on ballistic performance of glass composite laminates P Ram Subba Red y a * , T Sreekantha Reddy a , K Mogulan a a , G Seshagiri Rao a , Vemuri Madhu a , K Venkateswara Rao b a Armour Division, Defence M tallurgical Research Laboratory, Hyderaba -58, India b Jawaharlal Nehru Technological University, Hyderabad – 72, India Abstract In the present study varying thickness of (5-25mm) E-glass composit laminates have been prep red through hot compression moulding m thod using different matrix systems su h as phenolic and epoxy with E-glass fiber as a common reinforcement. The laminates were initially evaluated for their mechanical and mode-I inter laminar fracture en rgy as per ASTM test methods. It is observed that the laminate having epoxy matrix has shown higher mechanical and fracture energy than the laminate made using phenolic matrix. This is due to the strong adhe ion bond between the epoxy matrix and gla s fiber reinforcement. Further, the laminates were subjected to ballistic impact tests against 7.62X 39 mild steel projectiles. It is observed that the laminate having low r fracture e rgy (E-glass/phenolic) has shown better nergy absorption under b llistic impact. Failu e analysis on post i pacte laminates have been studied usi C-scan analysis a d obse ved that E-glass/epoxy composite laminat has shown limited damage area, whereas E-glass/phenolic composite laminate has shown more damage area. This study reveals that the laminate having lower fracture energy for delamination is more suitable for higher energy absorption due to dissipation of energy in lateral directions under ballistic impact conditions. © 2018 The Authors. Published by Elsevier B.V. This is a 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. © 2016 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of PCF 2016. Keywords: E-glass composite laminate; Fracture toughness; Impact tests; Damage area; Keywords: E-glass composite laminate; Fracture toughness; Impact tests; Damage area;

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

* Corresponding author. Tel.: +91-40-24588011; fax: +91-40-24588504. E-mail address: rsreddy@dmrl.drdo.in * Correspon ing author. Tel.: +91-40-24588011; fax: +91-40-24588504. E-mail address: rsreddy@dmrl.drdo.in

2452-3216 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. Publi hed by Elsevier B.V. This s op n access articl u der 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. © 2018 The Authors. Published by Elsevier

* 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.2019.05.084