PSI - Issue 14

ScienceDirect Available online at www.sciencedirect.com Available online at www.sciencedire t.com ienceDirect Structural Integrity Procedia 00 (2016) 000 – 000 Procedia Structu al Integrity 14 (2019) 375–383 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. 2nd International Conference on Structural Integrity and Exhibition 2018 Fatigue Analysis of Wing-Fuselage Lug section of a Transport Aircraft K.Shridhar 1 , B.S.Suresh 1 , M.Mohan Kumar. 2* 1 Department of Mechanical Engineering, B M S College of Engineering, Bangalore- 500 019. 2 Fatigue & Structural Integrity Group, Structural Tech ologies Division CSIR-National Aerospace Laboratories, Bangalore 560 017. * Corresponding author: Email-Id: mmk@nal.res.in, Phone: +91-(0)80- 2508 6325 Abstract Lug joints are special type of pin joints, which are widely used for joining various parts of an aircraft, especially for joining wings to fuselage. During service, the lug type joints are subjected to fatigue loading and complete load transfer takes place through the pin. At the pin and lug interface, the combination of high stress concentration and fretting could potentially lead to crack initiation and then crack propagation under cyclic loading. Because of this reason the wing-fuselage lug joints are considered as most fracture critical components in the aircraft structure. To appraise the safety level of lugs under working conditions, fatigue crack growth and residual life data are required.In the present work, a computational model for estimating the residual fatigue life of attachment lugs has been proposed. The pin is assumed to have a larger stiffness than the lug. The pin is assumed to be fit in the lughole with zero clearance and no frictional restraint. Initially stress concentration effects in the loaded lug were determined by applying analytic l and numerical meth ds. Stress inte sity factor for the pin loaded lug with through the-thickness emanating from the lug hole has been determined. Both analytical and numerical methods have been us d for obtain g the stress intensity fac or. Further, fat gue crack growth life for the cracked lug subjected to constant amplitude cyclic loading was estimated using the Walk r’s crack growth model. Also the effect of different radius ratios (lug g ometry) on the number of cycles to failure is studied. For the FE analysis MSC Nastra /Patran softwar s have b en used. © 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 Fatigue Analysis of Wing-Fuselage Lug section of a Transport Aircraft K.Shridhar 1 , B.S.Suresh 1 , M.Mohan Kumar. 2* 1 Department of M chanical Engine ring, B M S College of Engineering, Bangal re- 500 019. 2 Fatigue & Structural Integrity Group, St uctur l Technologies Division CSIR-National Aerospace Laboratories, Bangalore 560 017. * Corresponding author: Email-Id: mmk@nal.res.in, Phone: +91-(0)80- 2508 6325 Abstract Lug joints ar special type of pin joints, which are widely sed for j inin vari us parts of an aircraft, especially for joining wings to fuselage. During service, the lug type joints are subjected to fatigue loading a d complete load transfer takes place through the pi . At the pin and lug interface, the combination of high stres concentration a d fretting could potentially lead to rack initiation and then crack propagati under cyclic loading. Because of this reason the wing-fusela e lug joints are s dered as most fractu e critical components in the aircraft structure. To appraise the safety level of lugs under working con itions, fatigue crack growth and residual life data are required.In the present work, computatio al model for estimating the re idual fatigue life of attac m nt lugs has been proposed. The pi is assumed to have a larger stiff ess than the lug. The pin is assu ed to b fit in the lughole with zero clearan e nd no fricti nal straint. I itially stress concent ation ff cts in the l ade lug were determined by apply ng analytica and numerical etho s. Stress intensity fa tor f he pi loaded lug with through the-thickness man ting from the lug hole has be n determined. Both analytical and numeri al method have been used for obta i the tress intensity factor. Fur her, fatigue crack growth ife for the racked lug subjected to constant ampli ude cyclic loading was stimat d using the Walker’s cr k growth m del. Also the effect of diffe ent radius ratios (lug geom try) on the nu ber of cycles to failure is studied. For the FE analysis MSC Nastran/Patran softwares have been used. © 2018 The Authors.Published by Elsevier B.V. This is an open access article under the CC BY-NC-ND license (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. © 2016 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of PCF 2016. © 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. Keywords: High Pressure Turbine Blade; Creep; Finite Element Method; 3D Model; Simulation. Keywords: Lug joint,Fatigue crack growth life,MSC Patran/Nastran

Keywords: Lug joint,Fatigue crack growth life,MSC Patran/Nastran

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 Th 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 an 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

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.2019.05.046