PSI - Issue 13

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 13 (2018) 89 –895 Available online at www.sciencedirect.com ScienceDirect Structural Integrity Procedia 00 (2018) 000 – 000 Available online at www.sciencedirect.com ScienceDirect Structural I tegrity 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. © 2018 The Authors. Published by Elsevie B.V. Pe r-r v ew und r responsibility of the ECF22 organiz r . ECF22 - Loading and Environmental effects on Structural Integrity In-situ measurement of near-tip fatigue crack displacement variation in laser melting deposited Ti-6.5Al-3.5Mo-1.5Zr-0.3Si titanium alloy Yanzeng Wu, Rui Bao*, Shaoqin Zhang Institute of Solid Mechanics, Beihang University, Beijing 100191, China Abstract Laser melting deposition (LMD) is an attractive additive manufacturing technique for fabricating titanium alloy components. A variety of distinct layer bands, heat affected bands (HABs), were found in the LMDed sample, which lead to a periodic fluctuation in the fatigue crack growth rate. In this paper, an in-situ fatigue testing was performed to investigate the crack tip opening displacement (CTOD) vari tio withi a full loading cycle. D gital image correlation (DIC) technique was implemented for obtaining the displacement fields at the vicinity of the crack tip. The crack closure phenomenon is observed from the CTOD variation and the crack opening stress level is different between HAB and non-HAB zone. Another key difference between HAB and non-HAB zone is the value of CTOD when the crack is opening. Besides, the variation of the CTOD loop and its influence on fatigue crack growth rate were also discussed in detail. © 2018 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the ECF22 organizers. Keywords: In-situ; Crack tip opening displacement; Laser melting deposition; Digital image correlation. 1. Introduction Additive manufacturing (AM) techniques have recently become emerging material processing technologies since metallic components can be directly built from computer-aided design models. AM is a potential solution in fabricating metallic parts with complex geometry and high strength due to its unique advantages, e.g. high processing precision and material utilization ratio, excellent geometrical flexibility of designed part (Olakanmi et al. (2015)). Laser melting deposition (LMD), one of the main AM techniques, is very suitable to manufacture large metal components, including titanium alloy components which are difficult to fabricate by traditional wrought-based process (Ren et al. (2015)). ECF22 - Loading and Environmental effects on Structural Integrity In-situ measurement of near-tip fatigue crack displacement variation in laser m lting d posited Ti-6.5Al-3.5Mo-1.5Zr-0.3Si titanium alloy Yanzeng Wu, Rui Bao*, Shaoqin Zhang Institute of Solid Mechanics, Beihang University, Beijing 100191, China Abstract Laser melting deposition (LMD) is an attractive additive manufacturing technique for fabricating titanium alloy components. A v ri ty of distinct layer bands, he t affected b n s (HABs), were found in the LMDed sample, which lead to a periodic fluctuati n in the fatigue crack growth rate. In this paper, an in-situ fatigue testing was perfor ed to investigate the crack tip opening displacement (CTOD) variation withi a full loading cycle. Digital image correlation (DIC) tech ique was implemented for obtaining th displacement fields at the vicinity of the crack tip. The crack closure phenomenon is observed from the CTOD variation a d t crack opening stre s level is different b tween HAB and non-HAB zone. Another key differ nce between HAB and non-HAB zone is the value of CTOD when the crack is opening. Besides, the variation of the CTOD loop and its influence o fatigue crack growth rate were also discuss d in det il. © 2018 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the ECF22 organizers. Keywords: In-situ; Crack tip opening displacement; Laser melting deposition; Digital image correlation. 1. Introduction Additive manufacturing (AM) techniques have recently become emerging material processing technologies since metallic components can be directly built from computer-aided design odels. AM is a potential solution in fabricating etallic parts with complex geometry and high strength due to its unique advantages, e.g. high processing precision and material utilization ratio, excellent geometrical flexibility of designed part (Olakanmi et al. (2015)). Laser melting deposition (LMD), one of the main AM techniques, is very suitable to manufacture large metal components, including titanium alloy components which are difficult to fabricate by traditi nal wrought-based process (Ren et al. (2015)). © 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.: +86-10-82339233. E-mail address: rbao@buaa.edu.cn * Corresponding author. Tel.: +86-10-82339233. E-mail ad ress: rba @buaa.edu.cn

* Corresponding author. Tel.: +351 218419991. E-mail address: amd@tecnico.ulisboa.pt 2452-3216 © 2018 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the ECF22 organizers. 2452-3216 © 2018 The Authors. Published by Elsevier B.V. Peer review under r sponsibility of the ECF22 organizers.

2452-3216 © 2016 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of PCF 2016.

2452-3216  2018 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the ECF22 organizers. 10.1016/j.prostr.2018.12.168