PSI - Issue 3

ScienceDirect Available online at www.sciencedirect.com Av ilable o line at ww.sciencedire t.com Sci ceDirect Structural Integrity Procedia 00 (2016) 000 – 000 Procedia Structu al Integrity 3 (2017) 162–167 Available online at www.sciencedirect.com ScienceDirect Structural Integrity Procedia 00 (2017) 000–000 il l li t . i i t. 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. Copyright © 2017 The Authors. Published by El evier B.V. This is an open access i le under th CC BY-NC-ND license (http://creativecommons.org/licenses/by-n -nd/4.0/). Peer-review under responsibility of the Scientific Committee of IGF Ex-Co. XXIV Italian Group of Fracture Conference, 1-3 March 2017, Urbino, Italy Fatigue behavior of innovative alloys at elevated temperature F. Berto a,* , P. Gallo b , S.M.J. Razavi a , M.R. Ayatollahi c a Department of Mechanical and Industrial Engineering, Norwegian University of Science and Technology (NTNU), Richard Birkelands vei 2b, 7491, Trondheim, Norway. b Department of Mechanical Engineering, Aalto University, Marine Technology, Puumiehenkuja 5A, Espoo 02150, Finland. c Department of Mechanical Engineering, Iran University of Science and Technology, Narmak, 16846, Tehran, Iran. Abstract The present paper summarizes the results from uniaxial-tension stress-controlled fatigue tests performed at different temperatures up to 650°C on Cu-Be and 40CrMoV13.9 specimens. Two geometries are considered: hourglass shaped (both materials), plates weakened by a central hole (Cu-Be alloy). The motivation of the present work is that, at the best of authors’ knowledge, only a limited number of works on these alloys under high-temperature fatigue are available in the literature and no results deal with notched components. In the present contribution, after a brief review of the recent papers, material properties and experimental procedure are described. The new data fro un- otched and notched s ecimens are summarized i th corresponding fatigue curves. The Cu Be specimens fati ue data are re-analysed in terms of the mea val e of the Strain E ergy Density (SED). The approach, successfully used by the same authors to summarise fatigue data from notched specimens made of different materials tested at room temperature, is extended here for the first time to high-temperature fatigue. In the plates with central holes the SED is evaluated over a finite size control volume surrounding the highly stressed zone at the hole edge. A value of the radius equal to 0.6 mm seems to be appropriate to summarize all fatigue data in a quite narrow scatter-band. Thanks to the SED approach it is possible to summarise in a single scatter-band all the fatigue data, independent of the specimen geometry. © 2017 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of IGF Ex-Co. e , a t t f i l I t i l i i , i i it f i l ( ), i i l i , , i , . b t t f i l i i , lt i it , i l , i j , , i l . c t t f i l i i , I i it f i l , , , , I . Abstract t summ i t lt i i l t i t t ll ti t t t i t t t t . i . t i i : l t t i l , l t t l l ll . ti ti t t i t t, t t t t l , l li it t ll i t t ti il l i t lit t lt l it t t . t t t i ti , t i i t t , t i l ti i t l i . t t t i i i t i ti . i ti t l i t t l t t i it . , ll t t t i ti t t i i t t i l t t t t ature, is extended here for th i t ti t i t t ti . t l t it t l l t i l t i it i t l l i t i l t ssed zone at the hole edge. A value of the radius equal to . t i t t i ll ti t i it tt . t t it i i l t i i i l tt ll t ti t , i t t specimen geometry. © 201 t . li l vier B.V. i i ilit t i ti i itt .

© 2016 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of PCF 2016. Keywords: high-temperature fatigue; copper-cobalt-beryllium alloy; fatigue strength; notched specimens; 40CrMoV. y : i -t rature fatigue; copper-cobalt-beryllium alloy; fatigue strength; notched specimens; 40CrMoV.

Keywords: High Pressure Turbine Blade; Creep; Finite Element Method; 3D Model; Simulation.

* Corresponding author. Tel.: +47-735-93831. E-mail address: filippo.berto@ntnu.no * rr i t r. l.: - - . - il : fili . rt t .

* 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 IGF Ex-Co. l i r . . i i ilit t i ti i itt . - t r . li

2452-3216 © 2016 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of PCF 2016. Copyright © 2017 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 IGF Ex-Co. 10.1016/j.prostr.2017.04.029