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) 704–711 Structural Integrity Procedia 00 (2016) 000–000 Structural Integrity Procedia 00 (2016) 000–000 ScienceDirect ScienceDirect Available onlin at www.sciencedirect.com

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www.elsevier.com/locate/procedia 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, Catan a, Italy Engineering Framework To Transfer The Minimum Fracture Toughness In The DBTT Region Between SE(B) And 1T CT Specimens Toshiyuki Meshii a, *, Kenichi Ishihara b a Faculty of Engineering, University of Fukui, 3-9-1 Bunkyo Fukui, 910-8507, Japan b KOBELCO RESEARCH INSTITUTE, INC., 1-5-5 Takatsukadai, Nishi-ku, Kobe, Hyogo, 651-2271, Japan The test specimen size effect of fracture toughness J c of the material in the ductile-to-brittle transition temperature (DBTT) region is known to not be ignored. One practical method was to use the 1-inch thickness (1T) compact tension (CT) test specimen to integrity assessment of cracked structure. To support this practice, a method to convert J c obtained with other sized CT specimens is provided in ASTM E1921. On the other hand, a large number of fracture toughness test data have been collected for the single-edge notched bend (SE(B)) specimens. In order to practically use the SE(B) test data in engineering application, it is essential for converting J c obtained from different sized SE(B) specimen to the 1T CT specimen J c . In this paper, an engineering framework is proposed to convert minimum J c obtained from various sized SE(B) specimens to the minimum 1T CT specimen J c . The approach applies the modified Ritchie-Knott-Rice failure criterion, which predicts the onset of cleavage frac ure when the crack-opening  22 measured at a d stance from th crack-tip equal to fo r tim the crack-tip opening displacement  t , denoted as  22d , exceeds a critical value  22c , to the elastic-plastic finite lement results. In addition, this framework utilizes our rec nt finding that the J when  22d reaches the critical v lue  22c has a possibility to correspond to the minimum J c for a specified speci en configuration and material. The proposed framework has an advantage on t e point that it requires only stress-strain curve as an experimental data. The validity of the framework was demonstrated through the experimental results. © 2016 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of ECF21. 21st Eu opean Confer nce on Fracture, ECF21, 20-24 June 2016, Catania, Italy Engineering Framework To Transfer The Minimum Fracture Toughness In The DBTT Region Between SE(B) And 1T CT Specimens Toshiyuki Meshii a, *, Kenichi Ishihara b a Faculty of Engineering, University of Fukui, 3-9-1 Bunkyo Fukui, 910-8507, Japan b KOBELCO RESEARCH INSTITUTE, INC., 1-5-5 Takatsukadai, Nishi-ku, Kobe, Hyogo, 651-2271, Japan Abstract The test specimen size effect of fracture toughness J c of the material in the ductile-to-brittle transition temperature (DBTT) region is known t not be ignored. One ractical meth d was to use the 1-inch thickness (1T) compact tension (CT) test specimen to integrity assessment of cr ck structure. To support this practic , a method to convert J c obtained with other sized CT specimens is provided in ASTM E1921. On the other hand, a large number of fracture toughness test data have been collected for the single-edge notched bend (SE(B)) specimens. In order to practically use the SE(B) test data in engineering pplication, it is essential for converting J c obtained from different sized SE(B) specimen to the 1T CT specimen J c . In this paper, an engine ring framework is proposed to onve t minimum J c obtained from various sized SE(B) specimens to the minimum 1T CT specim n J c . The approach applies the modified Ritchie-Knott-Ric failure criteri n, which predicts the onset of cleavage fracture when the crack-opening  22 m asured at a distance from th cr ck-tip equal to four times the crack-tip openi g displac m n  t , d noted as  22d , exceeds a critical value  22c , to the elastic-plastic finite element results. In addition, this framework uti izes ou recent finding that t J when  22d re ches the critical valu  22c has a possibility to correspond to th minimum J c for a s ecified specimen configuration and material. The proposed framework has an advantage on the point that it requires only stress-strain curve as an experim ntal data. The validity of the fra ework was demonstrated through the experimental results. 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. © 2016 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of ECF21. Abstract

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

* Corresponding author. Tel.: +81-776-27-8468; fax: +81-776-27-9764. E-mail address: meshii@u-fukui.ac.jp

* 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 ECF21. * Corresponding author. Tel.: +81-776-27-8468; fax: +81-776-27-9764. E-mail address: m hii@u-fukui.ac.jp

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.2016.06.091