PSI - Issue 13

ScienceDirect Available online at www.sciencedirect.com Available online at ww.sciencedire t.com Sci ceDirect Structural Integrity Procedia 00 (2016) 000 – 000 Procedia Structural Integrity 13 (2018) 102 –1 25 Available online at www.sciencedirect.com ScienceDirect Structural Integrity Procedia 00 (2018) 000–000 Available online at www.sciencedirect.com ScienceDirect Structural I t gri y 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. ECF22 - Loading and Environmental effects on Structural Integrity Effects of the building direction on fatigue crack growth behavior of Ti-6Al-4V manufactured by selective laser melting Wenbo Sun a ,Yu’e Ma a *, Xiaopeng Ai a ,Jianghai Li a School of Aeronautics, Northwestern Polytechnical University, Xi’an 710072, China b AVIC Chengdu Aircraft Design and Research Institute, Chengdu 610041, China Abstract Additive manufacturing selective laser melting (AM-SLM) are potential to be widely used in aircraft structural components. There are apparent layers along the building direction of titanium alloy samples manufactured by SLM. This will affect its fatigue properties. At present, few papers about effects of the building direction on fatigue crack growing behavior have been published. In this work, three kinds of titanium alloy Compact Tension (C(T)) specimens with different building directions were designed. Fatigue crack growth rate (FCGR) tests were performed. And fatigue crack growth rate versus stress intensity factor range ( da dN K   ) curves were obtained and then effects of the building direction on crack growth was analyzed. It is shown that FCGR of specimen with 90° building direction is the fastest, and then that of the 0° sample is slower, and 45° sample is the slowest. Fatigue life of 45° specimen is 1.49 times lon er and 1.46 times longer than that of 90° and 0° specimen se arately. Fracture mor holog of samples was studied. It shows that the fracture surface with 0° building direction is smooth and fatigue striations are observed. The fracture surface with 45° building direction has a slope along the thickness. The fracture surface of the sample with 90°is cluttered, and its building layers can be observed. But its fatigue striations are not clear. © 2018 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the ECF22 organizers. Keywords: Additive manufacturing selective laser melting; titanium alloy; building directions; fatigue crack growth; fracture surface 1. Introduction Compared with the t aditional manufac uring process, the sel ctive laser melting (SLM) technology has the advantages of increasing material utilization, shortening the processing period, and reducing the structure weight. It © 2018 The Aut ors. Published by Elsevier B.V. Peer-review under responsibility of the ECF22 organizers. ECF22 - Loading and Environmental effects on Structural Integrity Effects of the building direction on fatigue crack growth behavior of Ti-6Al-4V manufactured by selective laser melting Wenbo Sun a ,Yu’e Ma a *, Xiaopeng Ai a ,Jianghai Li b a School of Aeronautics, Northwestern Polytechnical University, Xi’an 710072, China b AVIC Ch ngdu Aircraft Design a d Research Institute, Chengdu 610041, China Abstract Additive manufacturing selective laser melting (AM-SLM) are potential to be widely used in aircraft structural components. There are apparent layers along the building direction of titanium alloy samples manufactured by SLM. This will affect its fatigu properties. t present, few papers about effects of the building direction on fatigue crack growing behavior have been published. In this work, thr e kinds of titanium alloy Compact Tension (C(T)) specimens with different building directions w re design . Fatigue crack growth rate (FCGR) tests were erformed. And fatigue crack growth rate vers s stress intensity factor rang ( da dN K   ) curves w re obtained and then effects of the building direction n crack growth was analyzed. It is shown that FCGR of specimen with 90° buildi g direction is th fastest, and then that of the 0° sample is slower, and 45° sample is the slowest. atigue life of 45° specimen is 1.49 times longer and 1.46 times longer than that of 90° and 0° specimen separately. Fracture morphology f samples was studied. It shows that the fracture surface with 0° building direction is smooth and fatigue stri tions are observed. The fracture surface with 45° building direction has a slope along the thickness. The fracture surface of the s mple with 90°is cluttered, and its building layers can be observed. But its fatigue striations are not clear. © 2018 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the ECF22 organizers. Keywords: Additive manufacturing selective laser melting; titanium alloy; building directions; fatigue crack growth; fracture surface 1. Introduction Compared with the traditional manufacturing process, the selective laser melting (SLM) technology has the advantages of increasing material utilization, shortening the processing period, and reducing the structure weight. It © 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 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. * Corresponding author. Tel.: +0-000-000-0000 ; fax: +0-000-000-0000 . E-mail address: ma.yu.e@nwpu.edu.cn * Corresponding author. Tel.: +0-000-000-0000 ; fax: +0-000-000-0000 . E-mail ad ress: ma.yu.e@nwpu.edu.cn

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.2018.12.190