PSI - Issue 14

ScienceDirect Available online at www.sciencedirect.com Av ilable o line at ww.sciencedire t.com ScienceDirect Structural Integrity Procedia 00 (2016) 000 – 000 Procedia Structural Integrity 14 9 44–52 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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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.2019.05.007 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 responsi ility of Peer-review under responsibility of the SICE 2018 organizers. 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. 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 Numerical Analysis and Effects on Rigidity of Combat Vehicle Structure Due to Blast Load D R Makwana a* , Dr D G Thakur b , K Senthilkumar a a DRDO-Vehicles Research & Development Establishment (VRDE), Ahmednagar 414006, India b Defence Institute of Advanced Technology (DIAT), Pune 411025, India Abstract Blast effects are severe especially in case of close underbelly blast events. The hull of the structure must resist the blast load with limited deformation and on the other hand it should have sufficient rigidity also to have optimised structural design. Numerical analysis revealed the peak deformation areas on the hull structure which were further stiffened by adding the stiffeners to control the peak deformation. In the analysis, the s r ss-time, pressure- ime and deforma ion-time graphs were also obtained for the blast ev nts for with and without adding stiffeners. Th optimised plate thi kness with limited deformation by means of stiffeners was obtained. Keywords: Spherical blast; blast analysis; mine blast; V-hull 1. Introduction The blast effects primarily depends on the impact of blast wave on the structure. The blast wave impinges on the hull bottom first and get transferr d to the vehicle structure. The parameters like stand-off, type of explosive, location of blast and des gn of hull bottom plays vi al role in neutralising the blast effectiveness of vehicle. The reduction in the momentum of blast can be achieved through increase in the stand-off, by reducing the internal angles of V-plate or by providing sharp V-angles and also by reducing the overall momentum by using counter momentum techniques. Bocchieri et al. shown the approach to carry out model simulation and the vital factors involved in the analysis. Ramasamy et al concluded that the most common blast mine is Anti-vehicular (AV) mines which is being used to blast the military vehicles. 2nd International Conference on Structural Integrity and Exhibition 2018 Numerical A alysis and Effects on Rigidit of Combat Vehicle Structure Due to Blast Load D R Makwana a* , Dr D G Thakur b , K Senthilkumar a a DRDO-Vehicles Research & Development Establishment (VRDE), Ahmednagar 414006, India b Defence Institute of Advanced Technology (DIAT), Pune 411025, India Abstract Blast effects are severe especially in case of close underbelly blast events. The hull of the structure must resist the blast load with limited deformation and on the other hand it should have sufficient rigidity also to have optimised structural design. Numerical analysis revealed the peak deformation areas on the hull structure which were further stiffened by adding the stiffeners to control the peak deformation. In th anal sis, th stress-time, p essure-time and deformation-tim g aphs were also obtained for the blast event for with and without adding stiffe ers. The optimised plat thickness with limited deformation by me ns of stiffeners w s obtained. Keywords: Spherical blast; blast analys s; mine blast; V-hull 1. Int oduction The blast effects primarily depends on the impact of blast wave on the structure. The blast wave impinges on the hull bottom first and gets transferred to the vehicle structure. The parameters like stand-off, type of explosive, location of last and desi n of hull bottom plays vital role i neutralising the blast effectiveness of vehicle. The reduction in the momentum of blast can b achieved through increase in the stand-off, by reducing the internal angles of V-plate or by providing sharp V-angles and also by reducing the overall momentum by using counter momentum techniques. Bocchieri et al. shown the appr ach to carry out model simulation and the ital factors involved in the analysis. Ramasamy et al concluded that the most common blast mi e is Anti-vehicular (AV) mines which is being used to blast the military vehicles. * Corre ponding author. Tel.: +0091-241-2544004; fax: +0091-241-2548164. E-mail address: drmakwana@vrde.drdo.in © 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.: +351 218419991. E-mail address: amd@tecnico.ulisboa.pt * Corresponding author. Tel.: +0091-241-2544004; fax: +0091-241-2548164. E-mail address: drmakwana@vrde.drdo.in