PSI - Issue 2_A

ScienceDirect Available online at www.sciencedirect.com Av ilable o line at ww.sciencedire t.com cienceDirect Structural Integrity Procedia 00 (2016) 000 – 000 Procedia Structu al Integrity 2 (2016) 697–703 Available online at www.sciencedirect.com ScienceDirect Structural Integrity Procedia 00 (2016) 000–000

www.elsevier.com/locate/procedia

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, Catania, Italy Engineering Framework to Transfer the Lower Bound Fracture Toughness between Different Temperatures in the DBTT Region Toshiyuki Meshii a, *, Teruhiro Yamaguchi b a Faculty of Engineering, University of Fukui, 3-9-1 Bunkyo, Fukui-shi, Fukui, 910-8507, Japan b Graduate Student, University of Fukui, 3-9-1 Bunkyo, Fukui-shi, Fukui, 910-8507, Japan In this paper, an engineering framework to transfer the lower bound fracture toughness between different temperatures in the ductile–to–brittle (DBTT) temperature region is proposed and validated for 0.55% carbon steel using 0.5TSE(B) specimens. The framework requires only stress–strain curve for different temperatures as experimental data. The approach was based on the authors’ finding that the critical stress σ 22c of the modified Ritchie–Knott–Rice criterion (the criterion predicts onset of cleavage fracture of a material in the DBTT transition temperature region, when the mid-plane crack-opening stress σ 22 measured at a distance from the crack-tip equal to four times the crack-tip opening displacement δ t , denoted as σ 22d , exceeds a critical value σ 22c ) seems to be correlated with the lower bound fractur oughness for a specific specimen configuration. The pr posed approa h is expected to ov rcome some inconveniences which recent studies have reported to the Master Curve Local approaches to cleavage fracture that the Weibull parameters vary with size and temperature and are different from those stated in the Master Curve. © 2016 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of ECF21. Keywords: lower bound toughness ; master curve ; modified Ritchie-Knott-Rice failure criterion ; temperature dependency Tos In this paper, an engineering framework to transfer the lowe t er 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. Abstract

© 2016 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of PCF 2016. Nomenclature

Nomenclature B

Specimen thickness

Keywords: High Pressure Turbine Blade; Creep; Finite Element Method; 3D Model; Simulation. Gross thickness of test specimens and of prediction B o , B x

* 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 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.2016.06.090