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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 Struc ural Integrity 2 (2016) 1335–1342

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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. a O ract p crack propag ucted to clarif gated and the cterized by the xperimental cr n a narrow ba eter of the cre nm and ~390 ness in the thic 16 The Author revi w under r ords: creep; crac troduction saka univesity, D ation experime y the cr ep cr propagation w stress intensit ack center open nd irrespective ep crack propa nm films, sugg kness range of s. Published by esponsibility o ck prop g tion; th nts on Au free ck propagatio as accompanie y factor. The s ing displacem of the specim gation rate in th esting that the from ~240 nm Elsevier B.V. f th Scientific in films, size ff standing films properties a d by creep de teady-state cre ent rate. The cr en width and e Au films. Fu creep crack pr to ~390 nm. Committee of E e ts, creep J-integ of ~240 nm a nd the thickn formation. The ep J-integral � � ∗ eep crack prop applied stress, rthermore, the opagation prop CF21. aral; gol nd ~390 nm th ss effects. In crack propag was estimated agation rate d� indicating tha d�⁄d� – � � ∗ relat erties of the A ka 565-0871, Jap ickness at roo ll the experim ation rate d�⁄d by an approxi �⁄d� vs. � � ∗ rela t � � ∗ was the d tions were close u films were in an m temperature ents, cracks � was not uni mate equation tions were obs ominant mecha to each other sensitive to the uki were sta ly quely using erved nical in the film e 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. Hi Abst Cree cond propa chara the e withi param ~240 thick © 20 Peer Keyw 1. In

crack prop gral � ∗ is the (LSC) condit 989)). The a

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© 2016 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of PCF 2016. rize the creep e creep J-inte

racture mech rimental stud propagation 6), Ohji et a

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

* C E

orresponding aut -mail address: hi

hor. Tel.: +81-6 rakata@mech.en

6879-7241; fax: g.osaka-u.ac.jp

+81-6-6879-7243

.

2452 Peer

3216 © 2016 Th review under r

e Authors. Publis esponsibility o

hed by Elsevier f the Scientific

B.V. Committee of E

CF21.

* 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 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.2016.06.170