PSI - Issue 14

ScienceDirect Available online at www.sciencedirect.com Av ilable o line at www.sciencedirect.com cienceDirect Structural Integrity Procedia 00 (2016) 000 – 000 Procedia Structu al Integrity 14 (2019) 475–481 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 Filler size effect on fracture behavior of milled-fiber composites M. K. Singh a , R. Kitey b * a Ph.D Student, Department of Aerospace Engineering, IIT Kanpur, Kanpur, 208016, India b Associate Professor, Department of Aerospace Engineering, IIT Kanpur, Kanpur, 208016, India Abstract Quasi static flexural and fracture tests are conducted on anhydride rich epoxy system reinforced with three different sizes of milled glass fibers, 1/32”, 1/8” and 1/4”. The matrix is prepared by mixing DGEBA resin and MTHPA hardener in equal ratio by weight whereas the 16  m diameter slender fillers are reinforced at 3% volume fraction. It is observed that the flexural modulus and fracture toughness increase monotonically with increase in the slender filler size whereas the flexural strength of composites decreases with increasing filler lengths. The largest fillers enhance the flexural modulus and fracture toughness of neat epoxy system by ~ 1.3 and ~ 3 times, respectively. It is suggested that in the presence of large slender fillers, fiber fracture is the dominant toughening mechanism whereas the smaller size fibers are subjected to pull-out in the fracture process © 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: Slender fillers; fracture toughness; filler size effect. 1. Introduction Filled polymer composites have wide variety of civil and defense applications. Becaus of igh specific st ngt and high specific stiffness their usage in automobi e and aviation industries h s grown manifold. While spherical or irregular shaped particles are often used to reinforce polymers, the slender filler reinforcement is not very common due to the involved processing complexities. Yesgat and Kitey (2016) used spherical fillers of 34 μm average diameter and milled-fibers of average length 200 µ m and 16 µm diameter to reinforce the epoxy and reported 2nd International Conference on Structural Integrity and Exhibition 2018 Filler size effect on fracture behavior of milled-fiber composites M. K. Singh a , R. Kitey b * a Ph.D Student, Department of Aerospace Engi eering, IIT Kanpur, Kanpur, 208016, India b Associate Professor, Department of Aerospace Engineering, IIT Kanpur, Kanpur, 208016, India Abstract Quasi tat c flexural and fracture tests are conducted on anhydride rich epoxy system reinforced with thre diff rent sizes of milled glass fibers, /32”, 1/8” and 1/4”. The matrix is prepa ed by mixing DGEBA resin and MTHPA harden r in equal ratio by weight wh reas t e 16  m diameter slender fillers are r inforced at 3% volum fraction. It i observed that the flexural odulu and fracture oughn s increase monotonically with incr a e in the slender filler size where s the flexural stre gth composites decr ases with increasing f ll r lengths. The large t fillers nhance the flexural modulus and fracture toughness of neat epoxy system by ~ 1.3 a d ~ 3 times, respectively. It is suggested that in the presence of large slender fille s, fiber fracture is the dominant toughening mechanism whereas the smaller size fibers are subjected to pull-out in the fracture process © 2018 The Authors. Published by Elsevier B.V. This is an 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. Keywords: Slender fillers; fracture toughness; filler size effect. 1. Introduction Filled polymer compo i es have wide variety of civil and defense applications. Because of high specific strength and high pecific stiffn s their usage in automobil and aviation industries has grown manifold. While spherical r irr gular shaped particles are often used to reinforce polymers, the slender filler reinforcement is not very common ue to the involv processing complexities. Yesgat and Kitey (2016) used spherical fillers of 34 μm average diameter and milled-fibers of average length 200 µ m and 16 µm diameter to reinforce the epoxy and reported © 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.: +91-512-259-7060. E-mail address: kitey@iitk.ac.in * Correspon ing author. Tel.: +91-512-259-7060. E-mail address: kitey@iitk.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.2019.05.057