PSI - Issue 5

ScienceDirect Available online at www.sciencedirect.com Av ilable o line at ww.sciencedire t.com cienceDirect Structural Integrity Procedia 00 (2016) 000 – 000 Procedia Structu al Integrity 5 (2017) 801–808 Available online at www.sciencedirect.com ScienceDirect Structural Integrity Procedia 00 (2017) 000–000 il l li t . i ir t. tructural Integrity rocedia 00 (2017) 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. © 2017 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of ICSI 2017 2nd International Conference on Structural Integrity, ICSI 2017, 4-7 September 2017, Funchal, Madeira, Portugal Fatigue damage analysis of wing-fuselage attachment lug Slobodanka Bo janovi ć a *, Stevan Mak imovi ć b a Mathematical Institute of the Serbian Academy of Sciences and Arts, Kneza Mihaila 36, Belgrade 11000, Serbia b VTI - Aeronautical Department, Ratka Resanovi ć a 1, Belgrade 11000, Serbia Abstract In the present paper, the fatigue behavior of failure critical pin-loaded lug with the through-the-thickness crack at a hole is analyzed. Such an investigation examines th stress analysis and the residual life estimation through a computational model here proposed in which suitable fracture mechanics concepts are employed. Hence, the stress ratio dependence crack growth model is taken into account to assess the fatigue strength of damaged lug. Further, in order to calculate the stress intensity factor, fracture mechanics based analytical and numerical approaches are applied. Finally, to demonstrate the compatibility of developed model, relevant experimental data are used. Such crack growth observations show a fairly good correlation with obtained failure assessments. © 2017 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of ICSI 2017. Keywords: Fatigue failure; pin-loaded lug; residual life estimation; stress analysis. 1. Introduction Aeronautical systems often contain the lug-pin joints that enable the transfer of loading capacity for stationary and moving service operations. However, under cyclic loading, the combination of high stress concentration, fretting and corrosion can cause a premature collapse of such a mechanical linkage, due to crack initiation and propagation. Therefore, to avoid any safety hazard related to a load transfer assembly, reliable computational models have to be developed for the fatigue failure analysis of through-the-thickness and/or surface crack situations. tr t r l I t rit , I I , - t r , l, ir , rt l l lj i a , t i i b a athe atical Institute of the Serbian cademy of Sciences and Arts, Kneza Mihaila 36, Belgrade 11000, Serbia b VTI - Aeronautical Department, atka esanovi ć a 1, elgrade 11000, Serbia str ct I t e rese t a er, t e fati e e a i r f fail re critical i -l a e l it t e t r -t e-t ic ess crac at a le is a al ze . c a i esti ati e a i es t e stress a al sis a t e resi al life esti ati t r a c tati al el ere r se i ic s ita le fract re ec a ics c ce ts are e l e . e ce, t e stress rati e e e ce crac r t el is ta e i t acc t t assess t e fati e stre t f a a e l . rt er, i r er t calc late t e stress i te sit fact r, fract re ec a ics ase a al tical a erical a r ac es are a lie . i all , t e strate t e c ati ilit f e el e el, rele a t e eri e tal ata are se . c crac r t ser ati s s a fairl c rrelati it tai e fail re assess e ts. e t rs. lis e lse ier . . Peer-review n er res si ilit f t e cie tific Committee of ICSI 2017. Key ords: atigue failure; pin-loaded lug; residual life esti ation; stress analysis. . I t ti r ti l s st s ft t t l - i j i ts t t l t tr sf r f l i it f r st ti r i s r i r ti s. r, r li l i , t i ti f i str ss tr ti , fr tti rr si s r t r ll s f s i l li , t r i iti ti r ti . r f r , t i s f t r r l t t l tr sf r ss l , r li l t ti l ls t l f r t f ti failure analysis of through-the-thickness and/or surface crack situations. © 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. I t r ti l f r

2452-3216 © 2016 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of PCF 2016. 2452-3216  2017 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of ICSI 2017 10.1016/j.prostr.2017.07.053 * Corresponding author. Tel.: +351 218419991. E-mail address: amd@tecnico.ulisboa.pt 2452-3216 © 2017 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of ICSI 2017. 2452-3216 2017 he uthors. ublished by lsevier . . eer-re ie er res si ilit f t e cie tific ittee f I I . * Corresponding author. Tel.:+381-63-805-6085; fax:+381-11-351-1282. E-mail address: slobodanka.boljanovic@gmail.com * orresponding author. el.: 381-63-805-6085; fax: 381-11-351-1282. - ail address: slobodanka.boljanovic g ail.co