PSI - Issue 5

ScienceDirect Available online at www.sciencedirect.com Av ilable o line at ww.sciencedire t.com ienceDirect Structural Integrity Procedia 00 (2016) 000 – 000 Procedia Structu al Integrity 5 (2017) 569–576 Available online at www.sciencedirect.com ScienceDirect Structural Integrity Procedia 00 (2017) 000 – 000 il l li t . i ir t. Structural Integrity Procedia 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. 2nd International Conference on Structural Integrity, ICSI 2017, 4-7 September 2017, Funchal, Madeira, Portugal Elasto-plastic TCD as a method of failure prediction Terekhina Alena a, *, Anastasiia K stina a , Plekhov Oleg a , S smel Luca b a ICMM UrB RAS, Academika Koroleva st, 1, Perm 614013, Russia b Department of Civil and Structural Engineering, The University of Sheffield, Sheffield S1 3JD, United Kingdom Development of the method for assessing the strength of engineering structures, considering the effects of the non-locality fracture in the area of stress co centrators, under different loading regime is one of the major scientific interests. In the present study the linear-elastic Theory of Critical Distances (TCD) is modificated for the case of elasto-plastic material behavior. The for plotting Johnson – Cook model was used for simulation of material behavior, and an elasto-plastic critical distance value was used in order to estimate the strength of the tested samples. The accuracy and reliability of the proposed design methodology was checked against experimental data: the cylindrical un-notched specimens and samples with stress concentrators of titanium alloy Grade2 were tested under tensile loading with different strain rate. Mechanical tests were carried out using a 300 kN electromechanical testing machine Shimadzu AG-X Plus and Gopkinson- Kolskiy’s split bar. The obtained results showed that the use of the modification of the TCD based on elasto-plastic material behavior gives us estimates falling within an error up to 12% which means that the elasto-plastic TCD gives more accurate predictions than the linear elastic TCD solution (when using of elastic stress information the error interval is ± 15-20%). © 2017 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of ICSI 2017. Keywords: Theory of Critical Distances; notches; static fracture; dynamic fracture; linear-elastic analysis elasto-plastic analysis tr t r l I t rit , I I , - t r , l, ir , rt l i l a, , t ii o ti a , l l a , u l a I r S, cade ika oroleva st, 1, Perm 614013, Russia b Department of Civil and Structural Engineering, The University of Sheffield, Sheffield S1 3J , nited ingdo str ct e el e t f t e et f r assessi t e stre t f e i eeri str ct res, c si eri t e effects f t e -l calit fract re i t e area f stress c nce trat rs, er iffere t l a i re i e is e f t e aj r scie tific i terests. I t e rese t st t e li ear-elastic e r f ritical ista ces ( ) is ificate f r t e case f elast - lastic aterial e a i r. e f r l tti J s el as se f r si lati f aterial e a i r, a a elast - lastic critical ista ce al e as se i r er t esti ate t e stre t f t e teste sa les. e acc rac a relia ilit f t e r se esi et l as c ec e a ai st e eri e tal ata: t e c li rical - tc e s eci e s a sa les it stress c ce trat rs f tita i all ra e ere teste er te sile l a i it iffere t strai rate. ec a ical tests ere carrie t si a electr ec a ical testi ac i e i a z - l s a i s - ls i ’s s lit ar. e tai e results showed t at t e se f t e ificati f t e ase elast - lastic material behavior gives us estimates falling within an error up to 12% which means that the elasto-plastic TCD gives more accurate predictions than the li ear elastic s l ti ( e si f elastic stress i f r ati the error interval is ± 15-20%). © 2017 The Authors. Published by Elsevier B.V. eer-re ie er res si ilit f t e cie tific ittee f I I . ey ords: heory of ritical istances; notches; static fracture; dyna ic fracture; linear-elastic analysis elasto-plastic analysis © 2017 The Authors. Published by Elsevier B.V. Peer-review und r responsibility of the Scientific Committee of ICSI 2017 Abstract I t r ti l f r

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© 2016 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of PCF 2016. 1. Introduction

Keywords: High Pressure Turbine Blade; Creep; Finite Element Method; 3D Model; Simulation. In situations of practical interest, real engineering components are characterized by complex geometries resulting in local stress concentration phenomena. They normally contain either notches or complex features that may generate I sit ti s f r ti l i t r st, r l i ri ts r r t ri l tri s r s lti i l l str ss tr ti . r ll t i it r t s r l f t r s t t r t

* Corresponding author. Tel.: +7-(342)-237-83-12. E-mail address: terekhina.a@icmm.ru * orresponding author. el.: 7-(342)-237-83-12. - ail address: terekhina.a ic .ru

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.2017.07.174 * 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 .