PSI - Issue 2_A

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 2 (2016) 728–735 Available online at www.sciencedirect.com ScienceDirect Structural Integrity Procedia 00 (2016) 000–000 il l li i 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 Applicability Of Modified Ritchie-Knott-Rice Failure Criterion To Predict The Onset Of Cleavage Fracture For The Test Specimen With Res dual Str ss Introduced To The Crack Tip Kenichi Ishihara a, *, Takeshi Hamada a , Naohiro Kikuya b and Toshiyuki Meshii c a KOBELCO RESEARCH INSTITUTE, INC., 1-5-5 Takatsukadai, Nishi-ku, Kobe, Hyogo, 651-2271, Japan b Graduate Student, University of Fukui, 3-9-1 Bunkyo, Fukui, Fukui, 910-8507, Japan c Faculty of Engin ering, Un versity of Fukui, 3-9-1 Bunkyo, Fukui, Fukui, 910-8507, Japan In this work, applicability of the modified Ritchie-Knott-Rice (RKR) failure criterion (which predicts the onset of cleavage fracture when the crack opening stress measured at four times the crack-tip opening displacement σ 22d exceeds a critical value σ 22c ) is demonstrated for the test specimen with residual stress. This was done by comparing the results of the fracture toughness test and elastic-plastic finite element analysis results. 0.45 % carbon steel JIS S45C, whose tensile to yi ld stress ratio was equal to 1.5 was chose as material fo the test. SE(B) specime of width 46 x thickness 23 mm, which complies the ASTM E1921 was used for the test. The residua stress was introduced to the crack-tip by mechanical pre-l ading. The results showed that though scatter of the fracture oughn ss J c was large, s tter of the critical valu σ 22c was very small. Thus, th modified RKR failur criterion has been shown to be app icable to the S45C SE(B) specimens of thicknes 23 mm with esidual st es by mechanical pre-loading. In addition, the J corresponding to the loa th t σ 22d irst reaches σ 22c seem d to predict t e lower bound toughness for the material and the specified specimen configuratio . © 2016 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of ECF21. a b c , ., , , , , , , , , , , , , i , , , , , e n r l t e e e onsibility if 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: Fracture toughness; Modified Ritchie-Knott-Rice failure criterion; Residual stress; SE(B) specimen Abstract

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

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* Corresponding author. Tel.: +81-78-992-5976; fax: +81-78-992-5830. E-mail address: ishihara.kenichi@kki.kobelco.com . . .

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* 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.

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.2016.06.094