PSI - Issue 14

ScienceDirect Available online at www.sciencedirect.com Av ilable o line at ww.sciencedire t.com ienceDirect Structural Integrity Procedia 00 (2016) 000 – 000 Procedia Structu al Integrity 14 (2019) 627–633 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 licens (https://creativecommons.org/licens /by-nc- d/4.0/) Selection and peer-revi w under responsibility of Peer-review under responsibility of the SICE 2018 organizers. 2nd International Conference on Structural Integrity and Exhibition 2018 Development of Mounting Bracket for CCS electronic unit of Armoured Fighting Vehicle N.Venkateswaran a *, R.Vinobakrishnan a , S.Senthur Nathan a a CVRDE,Avadi,Chennai,600 054, INDIA Abstract This paper describes the design and development of new mounting bracket replacing the old one. Commander Control station (CCS) is one of the accessories for the Armoured Fighting vehicle (AFV) sighting system and it is fitted on the mounting bracket in front of Commander’s station at turret roof plate of the AFV. It displays the thermal images of the Gunner’s main sight which is to monitor the Gunner Line of sight continuously by the Commander. During the trial, it was noticed that the existing CCS electronics units are malfunctioned. To know the cause of malfunction, it was planned to conduct the vibration analysis on the locations of CCS electronics units. Subsequently the level of vibration on all the locations were recorded and analyzed for various operating rack profiles. The pectrum plot of CCS location for all these rack profiles shows the overall vibration lev ls in the frequency band of 20- 2000 z are well within the qualifie limit. However the CCS electronics units show a resonance at 22.5 Hz in the lo er frequency band where the amplitude is maximum may be of concern for electronic unit’s mal functionality. Hence a new CCS unit of light weight compact and durable is planned to retro fitment with the new modified compact mounting bracket on AFV. The mounting bracket is designed in such a way that the natural frequency of the same bracket to be away from 0-100Hz. This is achieved, by carrying out, Structural, Shock and Response Spectrum analysis. 1. Introduction Commander Control station (CCS) is one of the accessories for the AFVs sighting system and it is fitted on the mounting bracket in front of Commander’s station at turret roof plate of the AFV. It displays the thermal images of 2nd International Conference on Structural Integrity and Exhibition 2018 Developm nt of M unting Bracket for CCS electronic unit of Armoured Fighting Vehicle N.Venkateswaran a *, R.Vinobakrishnan a , S.Senthur Nathan a a CVRDE,Avadi,Chennai,600 054, INDIA Abstract This paper describes the design and development of new mounting bracket replacing the old one. Commander Control station (CCS) is one of the accessories for the Armoured Fighting vehicle (AFV) sighting system and it is fitted on the mounting bracket in front of Comm nd r’s station at turret roof plate of the AFV. It displays the thermal images of the Gunner’ main sight which is to monitor the Gunner Line of sight continuously by the Commander. During the trial, it was noticed that the existing CCS electronics units are malfunctioned. To know the cause of malfunction, it was planned to conduct the vibration analysis on the locations of CCS electronics units. Subsequently the level of vibration on all the locations were recorded and analyzed for various operating track profiles. The spectrum plot of CCS location for all these track profiles shows the overall vibration levels in the frequency band of 20- 2000Hz are well within the qualified limit. Howev r the CCS electronics units show a r sonance at 22.5 Hz in the ow r frequency band wh re the amplitude is maximum may be of concern for electronic unit’s mal functionality. Hence a new CCS unit of light weight compact and durable is planned to retro fitment with the new modified c mpact mounting bracket on AFV. The mounting bracket is designed in such a way that the natural frequency of the same bracket to be away from 0-100Hz. This is achieved, by carrying out, Structural, Shock and Response Spectrum analysis. Keywords: CCS; Frequency; track profile; mounting bracket; spectrum analysis; 1. Introduction Commander Control station (CCS) is one of the accessories for the AFVs sighting system and it is fitted on the mounting bracket in front of Commander’s station at turret roof plate of the AFV. It displays the thermal images of © 2016 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of PCF 2016. Keywords: CCS; Frequency; track profile; mounting bracket; spectrum analysis; Keywords: High Pressure Turbine Blade; Creep; Finite Element Method; 3D Model; Simulation.

* Corresponding author. Tel.:+ 91-944-494-7188; fax:.+ 044-2638-3882 E-mail address: venkateswaran.n@cvrde.drdo.in

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.2019.05.077 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 n open acc ss rticle 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. * Corresponding author. Tel.: +351 218419991. E-mail address: amd@tecnico.ulisboa.pt * Corresponding author. Tel.:+ 91-944-494-7188; fax:.+ 044-2638-3882 E-mail address: venkateswaran.n@cvrde.drdo.in