PSI - Issue 3

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 3 (2017) 191–20 Available online at www.sciencedirect.com ScienceDire t Structural Integrity Procedia 00 (2017) 000–000 Available online at www.sciencedirect.com ScienceDirect Structural Integrity Procedia 00 (2017) 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. Copyright © 2017 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 IGF Ex-Co. XXIV Italian Group of Fracture Conference, 1-3 March 2017, Urbino, Italy On the us of th Peak Stress Method for the calculation of Residual Notch Stress Intensity Factors: a preliminary investigation P. Ferro a , M. Colussi a, *, G. Meneghetti b , F. Berto c , M. Lachin a , S.A. Castiglione a a Department of Engineering and Management, University of Padova, Stradella San Nicola 3, 36100 Vicenza, Italy b Department of Industrial Engineering, University of Padova, Via Venezia 1, 35131 Padova, Italy c NTNU, Department of Engineering Design and Materials, Richard Birkelands vei 2b, 7491, Trondheim, Norway Abstract Residual stresses induced by welding processes significantly affect the engineering properties of structural components. If the toe region of a butt-welded joint is modeled as a sharp V-notch, the distribution of the residual stresses in that zone is asymptotic with a singularity degree which follows either the linear-elastic or the elastic plastic solution, depending on aspects such as clamping conditions, welding parameters, material and dimension of plates. The intensity f the local residual stress fields is quantified by the Residu l Notch Stress Intensity Fact rs (R NSIFs), which can b s d in principle to incl de the residu l stres effect in the fatigue assessmen of welded joints. Due to the need of extremely refined mes es and to the high computational res urces requi ed y non-linear transient analyses, the R-NSIFs have been calculated in literature only by means of 2D models. It is of interest to propose new coarse-mesh-based approaches which allow residual stresses to be calculated with less computational effort. This work is aimed to investigate the level of accuracy of the Peak Stress Method in the R-NSIFs evaluation. © 2017 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of IGF Ex-Co. Keywords: Peak Stress Method; Residual Stress; Finite Element Analysis; Residual Notch Stress Intensity Factor; Sysweld. 1. Introduction The prediction of failure in components and structures is not just an interesting research topic; it is an essential requirement for our daily live in safety, as pointed out by Miller (2003). There are many ways in which failures XXIV Italian Group of Fracture Conference, 1-3 March 2017, Urbino, Italy On the use of the Peak Stress Method for the calculation of Residual Notch Stress Intensity Factors: a preliminary investigation P. Ferro a , M. Colussi a, *, G. Meneghetti b , F. Berto c , M. Lachin a , S.A. Castiglione a a Department of Engineering and Management, University of Padova, Stradella San Nicola 3, 36100 Vicenza, Italy b Department of Industrial Engineering, University of Padova, Via Venezia 1, 35131 Padova, Italy c NTNU, e rt e t f Engineering Design and Materials, Richard Birkelands vei 2b, 7491, Trondheim, Norway Abstract Residual stresses induced by welding processes significantly affect the engineering properties of structural components. If the toe r gion of a butt-welded joint is modeled as a sharp V-notch, the dist ibution of the esidu stresses i that zone is asymptotic wi h a singulari y degre which follows either the linea -elastic r the lastic plastic solu ion, depending on aspects such as clamping conditions, we ding parameters, m teri l and dim nsion of tes. The intensity of the l cal residual stres fields s qua tified by the Residual Notch Stress Inte sity Factors (R NSIFs), which can be us d in principl o include the residual stress effect in the fatigu assessment of welded joints. Due to the eed of extremely refine meshes a o the high com utati al r s urc s required by non-linear tra sient analys s, the R-NSIFs have been calculated in iterature only by mea s of 2D models. It is of interest to propose new coarse-mesh-based approac es which allow r sid al stresses to be calculated with less c mputational eff rt. This ork i aimed to inv stigate t level of ccuracy of the Peak Stress Method i the R-NSIFs evalu . © 2017 T e Authors. Published by Elsevier B.V. Peer-review under espons bility of the Scientific Committee of IGF Ex-Co. Keywords: Peak Stress Method; Residual Stress; Finite Element Analysis; Residual Notch Stress Intensity Factor; Sysweld. 1. Introduction The prediction of failure in components and structures is not just an interesting research topic; it is an essential requir ment for our d y live in safety, a pointed o t by Miller (2003). There are m ny ways in which failures © 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.: +351 218419991. E-mail address: amd@tecnico.ulisboa.pt 2452-3216 © 2017 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of IGF Ex-Co. 2452-3216 © 2017 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of IGF Ex-Co. * Corresponding author. Tel.: +39 0444 998711; fax: +39 0444 998888. E-mail address: marco.colussi.1@phd.unipd.it * Corresponding author. Tel.: +39 0444 998711; fax: +39 0444 998888. E-mail address: marco.colussi.1@phd.unipd.it

2452-3216 © 2016 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of PCF 2016. Copyright © 2017 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 IGF Ex-Co. 10.1016/j.prostr.2017.04.037