PSI - Issue 14

ScienceDirect Available online at www.sciencedirect.com Av ilable o line at www.sciencedire t.com cienceDirect Structural Integrity Procedia 00 (2016) 000 – 000 Procedia Structu al Integrity 14 (2019) 337–344 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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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.2019.05.042 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. * Correspon ing author. Tel.: +91 471 2564913; fax: +91 471 2564038. # Currently at Space Application Centre, ISRO, Ahmedabad E-mail address: digendranath@gmail.com * Corresponding author. Tel.: +91 471 2564913; fax: +91 471 2564038. # Currently at Space Application Centre, ISRO, Ahmedabad E-mail address: digendranath@gmail.com 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 Residual stress measurement on 3-D printed blocks of Ti-6Al-4V using incremental hole drilling technique Digendranath Swain a, *, A. Sharma b,  , S. K. Selvan a , B. P. Thomas a , Govind b , J. Philip a a Experimental Mechanics Division(EXMD), STR Entity, Vikram Sarabhai Space Centre, ISRO, Thiruvananthapuram, India b Foundry Technology Division (FTD), MME Entity, Vikram Sarabhai Space Centre, ISRO, Thiruvananthapuram, India Abstract 3-D printing is envisaged to be a futuristic alternative for rapid and low-cost production of structural components. The major drawback in such fabrication processes is the occurrence of large magnitude of residual stresses (RS). RS are detrimental for the structural integrity of any component if it amplifies the service stresses beyond a limit. In this paper, RS measured using incremental hole drilling strain gauge technique on Direct Metal Laser Sintering (DMLS) 3-D printed prismatic blocks of Ti-6Al 4V has been reported in both non-heat treated and heat treated conditions. The results indicate that large tensile RS inherent in the non-heat treated blocks vanish after annealing. The extension of such mitigation plans to real-life structures and components must be planned so that the remaining service life is enhanced without any significant distortions and warpage. © 2018 The Aut ors. Published by Elsevier B.V. This is an open access arti le und r the CC BY-NC-ND license (https://cr ativecommons.org/licens s/by-nc-nd/4.0/) Selection and peer-review under responsibility of Peer-review under responsibility of the SICE 2018 organizers. Keywords: Additive manufacturing (AM); 3-D printing; DMLS; residual stresses (RS), incre ental hole drilling strain gage; Ti-6Al-4V 1. Introduction Additive manufacturing (AM), also known as 3-D printing ( ASTM F2792 − 12a ), is the process of manufacturing finished prod cts thru incremental layer-by-layer buildup of material using high-energy heat source and feedstock of metals. Additive manufacturing is classified into three major groups namely, Laser Beam Melting (LBM), Electron 2nd International Conference on Structural Integrity and Exhibition 2018 Residual stress measurement on 3-D printed blocks of Ti-6Al-4V using incremental hole drilling technique Digendranath Swain a, *, A. Sharma b,  , S. K. Selvan a , B. P. Thomas a , Govind b , J. Philip a a Experimental Mechanics D v sion(EXMD), STR Entity, Vikram S rabhai Space Centre, ISRO, Thiruv anthapuram, India b Foundry Technology Division (FTD), MME Entity, Vikram Sarabhai Space Centre, ISRO, Thiruvananthapuram, India Abstract 3-D printing is envisaged to be a futur tic alternative for rapid and low-cost pro ction of structural components. The major drawback such fabrication processes s the occurr nce of la ge magnitude of residua stresses (RS). RS are detrimental for the structural integrity of any compon nt if it amplifies the s rvice st esses beyond a limit. In this aper, RS mea ured using incremental hole drilli g strai gauge technique on Direct Metal Laser Sintering (DMLS) 3-D printed prismatic blocks of Ti-6Al 4V has been r ported in both non-he t treated and h a treated conditions. The results indic te that large t nsile RS inher in the non-heat treated blocks van sh aft annealing. The extension f such mitigation plans real-life st uctures and components must be plan ed so that the remaining service li e is enhan ed without any signifi ant distortion and warpage. © 2018 The Authors. Published by Elsevier B.V. This is a open access article under th CC BY-NC-ND lic nse (https://cre t 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: Additive manufacturing (AM); 3-D printing; DMLS; residual stresses (RS), incremental hole drilling strain gage; Ti-6Al-4V 1. Introduction Additive manufacturing (AM), also known as 3-D printing ( ASTM F2792 − 12a ), is t process of manufacturing finished products thru in remental layer-by-layer buildup of material using high-energy heat source and feedsto k f metals. Additive manufacturing is classified into three major groups na ely, Laser Beam Melting (LBM), Electron © 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