PSI - Issue 2_A

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ScienceDirect Available online at www.sciencedirect.com Av ilable o line at ww.sciencedire t.com ScienceDirect Structural Integrity Procedia 00 (2016) 000 – 000 Procedia Structu al Integrity 2 (2016) 066– 71 Structural Integrity Procedia 00 (2016) 000–000 tr t r l I t rit r i ( )

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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. 21st European Conference on Fracture, ECF21, 20-24 June 2016, Catania, Italy Discussion of the Stress Ratio Effect on the Fatigue Delamination Growth Characterization in FRP Composite Structures W. Hu 1 *, R. Jones 1 and A. J. Kinloch 2 1 Centre of Expertise for Structural Mechanics, Department of Mechanical and Aerospace Engineering, Monash University, Clayton, Victoria, 3800, Australia 2 Department of Mechanical Engineering, Imperial College London, Exhibition Road, London SW7 2AZ, UK The strain energy release rate (SERR) is widely used to study delamination growth in composites and adhesively bonded structures. Both the maximum SERR (G max ) and the range of SERR ( Δ G) are commonly used to characterize delamination growth rate. The present paper discusses the appropriateness of using the SERR range to characterize delamination growth in fibre reinforced plastic (FRP) composite structures, and several inconsistent results associated with fatigue tests reported in the open literature will be presented. To this end, the paper focuses on the question of ‘similitude’ and the potential for using the terms Δ ′ and ∆√ as alternativ methods for characterizing Mode I, Mod II and Mixed mode I/II delam ati n growth. © 2016 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of ECF21. Keywords: Crack driving force, fatigue crack growth, stress ratio, FRP composites, Δ G 1. Introduction Since Paris, Gomez, & An erson (1961) introduced the concept of using the range of stress intensity factor, ΔK, as th crack driving force (CDF) to character ze the cyclic atigue crack growth rate per cycle, da/dN, for aluminium alloy, ΔK has become one of the most widely used parameters for characterizing the fatigue performance of metallic materials (Schutz, 1996). It is generally known that in a thin layer of polymeric matrix sandwiched between two 1 1 2 1 t f ti f t t l i , t t f i l i i , i it , l t , i t i , , t li 2 t t f i l i i , I i l ll , i iti , , t i l t i i l t t l i ti t i it i l t t . t t i a t l t t i l i ti t t . t i t i t i t t t i l i ti t i i i l ti it t t , l i i t t lt i t it ti t t t i t lit t ill t . t i , t t ti i ilit t t ti l i t t ′ lt ti t t i i , i / l ti t . t . li l i . . Peer-revi w under responsi ility t i ti i itt . : r ri i f r , f ti r r t , tr r ti , it , 1. Introduction , , d , , i f , , , , . Copyright © 2016 The Authors. Published by Elsevier B.V. This is an open access article under the CC BY-NC-ND license (http://creativecommons.org/licenses/by-nc-nd/4.0/). Peer-review under responsibility of the Scientific Committee of ECF21. © 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

* Corresponding author. Tel.: +61-425-889-992 E-mail address: wenchen.hu@monash.edu i t r. l.: - - - - il : . . rr

* 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 ECF21. t r . li l i r . . i i ilit t i ti i itt . -

2452-3216 © 2016 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of PCF 2016. Copyright © 2016 The Authors. Published by Elsevier B.V. This is an open access article under the CC BY-NC-ND license ( http://creativecommons.org/licenses/by-nc-nd/4.0/ ). Peer review under responsibility of the Scientific Committee of ECF21. 10.1016/j.prostr.2016.06.009