PSI - Issue 2_B

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ScienceDirect Available online at www.sciencedirect.com Av ilable o line at ww.sciencedire t.com Scie ceDirect Structural Integrity Procedia 00 (2016) 000 – 000 Procedia Struc ural Integrity 2 (2016) 2772–2779 Structural Integrity Procedia 00 (2016) 000–000

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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 Investigation on the rotational deformation of SEB specimens with various crack length to width ratio Tomoya Kawabata* a , Tetuya Tagawa b , Yoichi Kayamori c , Shuji Aihara a and Yukito Hagihara d a The University of Tokyo, Hongo7-3-1, Bunkyo, Tokyo 113-8656, Japan b JFE Steel Corporation, Chiba 260-0835, J pan c Nippon Steel & Sumitomo Metal Corporation, Amagasaki 660-0891, Japan c Formerly Department of Mechanical Engineering, Sophia University, Tokyo 102-8554, Japan Abstract A new CTOD calculation formula was proposed by using a correction factor for the blunted crack tip in the authors’ previous report[Kawabata et al(2016)], and the calculated CTOD by the formula significantly corresponded to the actual CTOD obtained by FE analysis in the wide range of specimen thicknesses. However, the use of the CTOD formula is limited to the frequently used crack depth-to-width ratio, a 0 / W , between 0.45 and 0.55, and this does not satisfy a strong demand for wider a 0 / W range. Meanwhile, ISO15653 covers a wider range of a 0 / W between 0.10 and 0.70, where J-based CTOD calculation formula has been specified in the annex-E of ISO15653. In this cont xt, the plastic hinge model was investigated for a 0 / W betwe n 0.05 and 0.70 by using FE analysis, and the analytical deformation of SEB specimens revealed that the plastic hinge model was applicable to the specimens even though their a 0 / W were out of the frequently used a 0 / W range from 0.45 and 0.55. Their rotational center points were almost steady when changing the applied load and the work hardening coefficient. © 2016 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of ECF21. Keywords: Toughness testing; Test standards; Crack tip opening displacement; Plastic hinge model; Rotational factor; Work hardening 1. Introduction In the previous wo k [Tagaw t al(2010)], authors have pointe out that n some cases there exists large amount of difference between CTOD values calculated from J-integral (ASTM E1290-2002) and those from the plastic a a a , Tetuya b c a Ha d Japan c g, Sophia University, Tokyo 102-8554, Japan used cra e © 2016 The Authors. Published by Elsevier B.V. r i Copyright © 2016 The Authors. Published by Elsevi r B.V. This i an open access article under the CC BY-NC-ND license (http://cr ativecommons.org/licenses/by-nc-nd/4.0/). Peer-review under responsibility f the Scientific Comm ttee 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.

* Corresponding author. Tel.: +81-3-5841-6517; fax: +81-3-5841-6517. E-mail address: kawabata@fract.t.u-tokyo.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 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.2016.06.346