PSI - Issue 14

ScienceDirect Available online at www.sciencedirect.com Av ilable o line at www.sciencedire t.com ScienceDirect Structural Integrity Procedia 00 (2016) 000 – 000 Procedia Structu al Integrity 14 (2019) 746–757 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 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 Understanding the Residual Stress in DMLS CoCrMo and SS316L sing X-ray diffraction Manojakumar Chimmat a, b , Dheepa Srinivasan b,* a Metallurgical and Materials Engineering, National Institute of Technology Karnataka, Surathkal b INTECH DMLS, Pvt. Ltd., Bengaluru Abstract Laser additive manufacturing (LAM) is the next in line revolutionary technology for various turbine applications, as an enabler of new designs and parts and during repair and refurbishment of service returned parts. In LAM process, residual stresses play a key role during component build up as well as while removing the components from the build plate, to ensure distortion free parts, as a standalone or as a hybrid build on an existing part. The present study comprises an experimental determination of residual stresses of two direct metal laser sintered (DMLS) alloys, CoCrMo and SS316L, using the X-ray diffraction sin 2 ψ technique. In both cases, the process parameters were optimized to result in dense (> 99.95%) samples. Surface residual stress measurements were carried out on the DMLS samples in the as printed condition and after heat treatment. While SS316L measured a surface tensile stress of 127 MPa, CoCrMo showed a tensile stress of 265 MPa, in the as printed condition. Upon grit blasting, both samples undergo a peening effect and record a compressive stress of 300-400 MPa. Heat treatment of SS316L at 650°C, tends to relieve these stresses and results in zero stress, whereas for CoCrMo there was a systematic variation in the response to heat treatment at different temperatures, correlating with the microstructural evolution. At 1050°C CoCrMo shows compressive stresses because of partial recrystallization and at 1150°C having a completely recrystallized microstructure comprising equiaxed grains of around 40 µm and a completely stress relieved condition. © 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 Understanding the Residual Stress in DMLS CoCrMo and SS316L using X-ray diffraction Manojakumar Chimmat a, b , Dheepa Srinivasan b,* a Metallurgical and Materials Engineering, National Institute of Technology Karnataka, Surathkal b INTECH DMLS, Pvt. Ltd., Bengaluru Abstract Laser additive manufacturing (LAM) is the n xt in line rev lutionary technology for various tu bine applications, a an enabler of new es gns and parts and uring repair nd refu bishment of service r turned parts. In LAM process, resi ual s resses play a key role during component buil up as well as while removing the components fr the build plate, to ensur distortion free parts, s a standalone r as a hybrid build on an existing p rt. The present study comprises an xpe imental determ ation of residual stresses of two dire t met l laser int d (DMLS) alloy , CoCrMo and SS316L, using the X- y diffraction sin 2 ψ t chniqu . In both c ses, the process para eters were op imized to r sult in dense (> 99.95%) samples. Surface residual str ss m asurements were carri d out on the DMLS samples in the as printed condition and fter heat treatment. While SS316L measured a surface tensile tress of 127 MPa, CoCrMo showed a tensil tres of 265 MPa, in the as prin ed condition. Upon grit blasting, bo h sampl s undergo a peening ffect a d record a compressive stress of 300-400 MPa. Heat treatment of SS316L at 650°C, tends to relieve these stress s and results in zero stress, hereas for C C Mo ther was a systematic variation in the re ponse to heat treatment at different tempe atures, correl ting with the microstructural volution. At 1050°C CoCrMo shows compressive stresses because of parti l recrystallization and at 1150°C having a completely recrystallized microstructure comprising equiaxed grains of around 40 µm and a completely stress relieved condition. © 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-nc-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: Residual stress; XRD- sin 2 ψ ; Additive Manufacturing; DMLS Keywords: Residual stress; XRD- sin 2 ψ ; Additive Manufacturing; DMLS Keywords: High Pressure Turbine Blade; Creep; Finite Element Method; 3D Model; Simulation.

* Corresponding author. Tel: +91-9980050667; E-mail: dheepasrinivasan6@gmail.com * Corresponding author. Tel: +91-9980050667; E-mail: dheepasrinivasan6@gmail.com

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.2019.05.093 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 under the CC BY-NC-ND lic nse (https://creativecommons.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