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) 889–895 Available online at www.sciencedirect.com ScienceDirect Structural Integrity Procedia 00 (2017) 000 – 000 il l li t . i ir t. i i 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. 2nd International Conference on Structural Integrity, ICSI 2017, 4-7 September 2017, Funchal, Madeira, Portugal DIC Study of Fatigue Crack Growth after Single Overloads and Underloads A. Eremin a,b *, S. Panin a,b , R. Sund r b,c , F. Berto d a Institute of Strength Physics and Material Science SB RAS, 2/4, pr. Akademicheskii, 634055, Tomsk, Russia b National Research Tomsk Polytechnic University, 30, pr. Lenina, 634050, Tomsk, Russia c BiSS (P) Ltd, 497E 14th Cross, 4th Phase, Peenya Industrial Area, Bangalore 560058, India d Norwegian University of Science and Technology, Høgskoleringen 1. 7491 Trondheim. Norway The paper describes near-tip experimental strain measurements under simple variable-amplitude loading. Local strain was estimated by means of Digital Image Correlation (DIC) technique using optical microscope equipped with digital camera. Fatigue crack g owth tests were performed on single edge crack tension specimens made of Al-Cu alloy under specially designed load sequences, which included baseline cycles, single overload or underload with measurement cycles for DIC. The main idea of the study is to compare strain response and shapes of hysteresis loops at the crack tip and crack wake. The obtai ed results suggest that COD values measured at the crack tip are significantly affected by both underload and overload, but the influence is different for each case. The bserved behavior is attributed to abrupt changes in Kop and ΔK th and their subsequent recovery to the basic level. © 2017 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of ICSI 2017. Keywords: crack closure; crack-tip blunting/re-sharpening; variable-amplitude loading; overload; underload. Fo most e gine ring applications fatigue crack growth and structure performance estimates are based on the experiments performed under cyclic loading with constant amplitude whereas real structures are subjected to random spectrum loading. Process of crack growth and therefore fatigue life of a component is affected by various factors, which in some cases could not be controlled or measured in-situ in order to estimate the residual life time. The search tr t r l I t rit , I I , - t r , l, ir , rt l . i a, , . i a, , . ,c , . t a Institute of Strength hysics and aterial Science S S, 2/4, pr. kade icheskii, 634055, o sk, ussia b ational esearch o sk olytechnic niversity, 30, pr. enina, 634050, o sk, ussia c iSS ( ) td, 497 14th ross, 4th hase, eenya Industrial rea, angalore 560058, India d or egian niversity of Science and echnology, øgskoleringen 1. 7491 rondhei . or ay Abstract e a er escri es ear-ti e eri e tal strai eas re e ts er si le aria le-a lit e l a i . cal strai as esti ate ea s f i ital I a e rrelati ( I ) tec i e si tical icr sc e e i e it i ital ca era. ati e crac t tests ere erf r e si le e e crac te si s eci e s a e f l- all er s eciall esi e l a se e ces, ic i cl e aseli e c cles, si le erl a r erl a it eas re e t c cles f r I . e ai i ea f t e st s t c are strai res se a s a es f steresis l at t e crac ti a crac a e. e tai e res l s s est t at al es eas re at t e crac ti are si ifica tl affecte t erl a a erl a , t t e i fl e ce is iffer t f r eac case. e ser e e a i is attri te t a r t c a es i a th a t eir s se t rec er t t e asic le el. e t rs. lis e lse ier . . Peer-re ie nder res si ilit f t e cie tific ittee f I I . ey ords: crack closure; crack-tip blunting/re-sharpening; variable-a plitude loading; overload; underload. . I t ti r st i eri li ti s f ti r r t str t r rf r sti t s r s t ri ts rf r r li l i it st t lit r s r l str t r s r s j t t r s tr l i . r ss f r r t t r f r f ti lif f t is ff t ri s f t rs, i i s s s l t tr ll r s r i -sit i r r t sti t t r si l lif ti . s r © 2017 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of ICSI 2017 © 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. Abstract 1. Introduction I t r ti l f r

* Corresponding author. Tel.: +7-382-228-6922. E-mail address: eremin_av@bk.ru * orresponding author. el.: 7-382-228-6922. - ail address: ere in_av bk.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.2017.07.120 * 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 .