PSI - Issue 14

ScienceDirect Available online at www.sciencedirect.com Available o line at www.sciencedire t.com ScienceDirect Structural Integrity Procedia 00 (2016) 000 – 000 Procedia Structu al Integrity 14 (2019) 176–183 Available online at www.sciencedirect.com ScienceDirect StructuralIntegrity Procedia 00 (2018) 000–000 Available online at www.sciencedirect.com ScienceDirect StructuralIntegrity 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 Th 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 Development of In-house Unidirectional Carbon/epoxy Prepregs and its Characterization for Aerospace Applications P R Krishna Mohan a* , Anil Kumar M a , Shiva Goutham kumar a , and P M Mohite a a Department of Aerospace Engineering, Indian Institute of Technology, Kanpur Abstract The primary objective of this work is to develop an in-house Unidirectional Carbon/Epoxy prepreg manufacturing technology suitable for Aerospace applications. Modifications were made to the existing in-house prepreg manufacturing facility to improve the quality of prepregs. Physical tests were carried out to assess the quality of prepregs. The mechanical tests have been performed at both prepregs and laminate level. To quantify the cure extent of epoxy (B-stage curing), fiber volume fraction in the prepreg SDT (Simultaneous differential scanning calorimeter and thermos-gravimetric analysis) is used. A plasma surface treatment has been performedon carbon fibers to improve surface roughness and induce functional groups to improve adhesion betwee carbon fibers a d epoxy resin. The effect f lasma on carbon fibers was studied by conducting FTIR to iden fy requir d functional group on reated and untreated fibers. Further tests performed t laminat level include matrix d gestion test, SDT. Using ASTM D2734, void volume fraction is estimated. A 0° laminate is prep re , and a tensi n test is performed to quantify modulus and the strength. Tension tests of [±45] S and 90° laminate were also conducted to check proper impregnation (fiber/matrix interfacial bonding strength). The ra terization of UD prepreg has given an in-depth insight into prepreg manufacturing technology and therefore, contributed to obtaining a good quality in-house prepreg. © 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 Development of In-house Unidirectional Carbon/epoxy Prepregs and its Characterization for Aerospace Applications P R Krishna Mohan a* , Anil Kumar M , Shiva Goutham kumar a , and P M Mohite a a Department of Aerospace Engineering, Indian Institute of Technology, Kanpur Abstract The prima y objectiv of this work is to devel p an in-house Unidirectio al Carbon/Epoxy prepreg manufacturing echnol gy suitable for Aerospace applications. Modifications were made to the existing in-h use prepreg manufacturi g facili y to improve the quality of pre gs. Physic l tests were carried out o assess th quality of prepregs. The mechanical t sts have been erformed at both prepregs an lami ate level. To quantify th cure extent of epoxy (B-stage curing , fiber volume fraction in th prepreg SDT (Simultaneous differential scanning cal rimeter and thermos-gravimetric a alysis) is sed. A lasma surface tr atment has been performedon ca bon fibers to improve surface oughn ss and induce fu ctional gro ps to improve adhesion b twe n carbon f be s and poxy r sin. he eff ct of plasma carbon fib rs was st di d by conduc ing FTIR to dentify required functional groups on treat d and untreated fib rs. Further t sts p rformed at laminat level include ma rix digestion test, SDT. Using ASTM D2734, void volume frac ion is estim ted. A 0° laminat is prepa ed and a t nsion test is performed o quantify modulus and the strength. T nsion tests of [±45] S and 90° laminates w re also conducted to ch ck proper impregnation (fiber/matrix interfacial bo ing strength). The characterization of UD prepreg ha giv n an in-depth insight into prepreg manufacturing technology and therefore, contributed to obtaining a good quality in-house prepreg. © 2018 The Authors.Published by Elsevier .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: Carbon/epoxy prepreg, Mechanical and Physical Characterization, Plasma treatment. Keywords: Carbon/epoxy prepreg, Mechanical and Physical Characterization, Plasma treatment. Keywords: High Pressure Turbine Blade; Creep; Finite Element Method; 3D Model; Simulation. * Corresponding author. Tel.: +91-812-767-7104; fax: +91-512-259-7561. E-mail address: prkmohan@iitk.ac.in * Corresponding auth r. Tel.: +91-812-767-7104; fax: +91-512-259-7561. E-mail address: prkmohan@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.2019.05.023