PSI - Issue 14

ScienceDirect Available online at www.sciencedirect.com Av ilable o line at www.sciencedire t.com ienceDirect Structural Integrity Procedia 00 (2016) 000 – 000 Procedia Structu al Integrity 14 (2019) 571–576 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 n open access article under the CC BY-NC-ND licens (https://creativecommons.org/licenses/by-nc-nd/4.0/) Selection and peer-review under responsibility of Peer-review under responsibility of th SICE 2018 organizers. 2 nd International Conference on Structural Integrity and Exhibition 2018 Interlaminar Fracture Toughness of Short Fibre Reinforced GFRP Laminates K. Chawla 1* , S. Ray-Chaudhuri 2 , R. Kitey 3 1 Ph.D. Student, Department of Civil Engineering, Indian Institute of Technology, Kanpur, 208016, India. 2 Associate Professor, Department of Civil Engineering, Indian Institute of Technology, Kanpur, 208016, India. 3 Associate Professor, Department of Aerospace Engineering, Indian Institute of Technology, Kanpur, 208016, India. Abstract The influence of reinforced short fibers on the interlaminar fracture toughness of unidirectional laminate is studied. The glass fiber laminates are fabricated by using neat as well as the reinforced epoxy resin system by hand lay-up technique. Double cantilever beam test in combination with modified beam theory is employed to determine the interlaminar fracture toughness ( G Ic ) of the laminates. The load vs. crosshead displacement plots indicates stable crack propagation during the tests with higher crack growth resistance in case of short fibre reinforced specimens. Optical images show that the addition of fillers enhances fiber bridging which results in ~ 26 % increase in the G Ic value of the laminate in the reinforced case. © 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 the responsibility of the SICE 2018 organizers. Keywords: Glass fibre reinforced composite; short fibres; fibre bridging; fracture toughness 2 nd International Conference on Structural Integrity and Exhibition 2018 Interlaminar Fracture Toughness of Short Fibre Reinforced GFRP Laminates K. Chawla 1* , S. Ray-Chaudhuri 2 , R. Kitey 3 1 Ph.D. Student, Department of Civil Engineering, Indian I stitute of Technology, Kanpur, 208 16, India. 2 Associate Professor, Department of Civil Engineering, Indian I stitute of Technology, Kanpur, 208 16, India. 3 Associate Professor, Department of Aerospace Engineering, Indian Institute of Technology, Kanpur, 208016, India. Abstract Th influe ce of reinfo ced short fibers on he int rlaminar fractu e toughness of unidir ctional laminate is studied. The glass fiber laminates ar fabricated by using neat as well s the reinforced epoxy resin system by hand lay-up technique. Double cantilever be test in combination with modified b am he ry s employed to determine the nterlaminar fracture toughness ( G I ) of the lamina es. The load vs. cr sshead displacement plots i dicates stable crack propagation dur ng the tests with igh r crack growth res stance in case of short fibr reinforced specimens. Optical mag s show that th addition of fillers enhances fiber bridging which results in ~ 26 % increase in the G Ic value of the laminate in the reinforced case. © 2018 The Authors. Published by Elsevier B.V. This is an open access article under the CC BY-NC-ND lic nse (https://c ativecommons.org/licenses/by-nc- d/4.0/) Selection and peer-review under responsibility of Peer-review under the responsibility of the SICE 2018 organizers. Keywords: Glass fibre reinforced composite; short fibres; fibre bridging; fracture toughness

© 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 2597247 E-mail address : komalc@iitk.ac.in * Corresponding author. Tel.: +91 512 2597247 E-mail address : komalc@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.2019.05.070