PSI - Issue 2_B

ScienceDirect Available online at www.sciencedirect.com Av ilable o line at ww.sciencedire t.com ScienceDirect Structural Integrity Procedia 00 (2016) 000 – 000 Procedia Struc ural Integrity 2 (2016) 1829–1836 Available online at www.sciencedirect.com ScienceDirect Structural Integrity Procedia 00 (2016) 000 – 000 Available online at www.sciencedirect.com ScienceDirect 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 NSIFs estimation based on the averaged strain energy density under in-plane mixed mode loading L. Pittarello a , A. Campagnolo b and F. Berto a,c* a Dept. of Management and Engineering, University of Padua, Stradella S. Nicola 3, 36100, Vicenza, Italy b Dept. of Industrial Engineering, University of Padua, Via Venezia 1, 35131, Padova, Italy c Dept. of Engineering Design and Materials, NTNU, Richard Birkelands vei 2b, 7491, Trondheim, Norway In this work three methods for the rapid calculation of the NSIFs, based on the averaged strain energy density (SED), are compared. The first method was proposed by Lazzarin et al. and it is based on the calculation of the SED averaged in two different control volumes centred at the notch tip. The second one instead was recently presented by Treifi and Oyadiji and it takes advantage of the strain energy density averaged within two control volumes (semi-circular sector) centred at the notch tip. Then a new method based on the evaluat on of the total and deviato ic strain energy density averaged over a c ntrol volume has been proposed. Finally, the described methods have been app ied to plates weake ed by diff r nt V-n tch geometri s: diamond-shap notch, square hole a d c ntral crack in plates of finite and infinite extension. The values of the NSIFs derived acco ding to Gross an Mendelson have been compared with those obtained by means of the approximate methods, by using coarse FE mesh s. © 2016 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of ECF21. Keywords: NSIFs; Strain energy density; control radius; mixed mode; FE analysis. 21st European Conference on Fracture, ECF21, 20-24 June 2016, Catania, Italy NSIFs estimation based on the averaged strain energy density under in-plane mixed mode loading L. Pittarello a , A. Campagnolo b and F. Berto a,c* a Dept. of Management and Engineering, University of Padua, Stradella S. Nicola 3, 36100, Vicenza, Italy b Dept. of Industrial i i , i it f , Via V nezia 1, 35131, Padova, Italy c Dept. of Engineering Design and Materials, NTNU, Richard Birkelands vei 2b, 7491, Trondheim, Norway Abstract In this work three methods for the rapid calculation of the NSIFs, based on the averaged strain energy density (SED), are compared. The first me od was proposed by Lazz rin et al. and it is based on the calculation of the SED averaged in two different control volumes cen re at the n tch tip. The second one instead was recently presented by Treifi and Oy diji an it takes advantage f the strain nergy density averaged wit in tw control volumes ( emi-circular c or) cent d at the notch tip. Then a new me hod based on the evaluatio of the total and deviat ri strain energy density averaged over a control volume has been proposed. Finally, the describ d me hods have been appl ed to plates weaken d by different V-notch eom tri s: diam nd-shaped otch, squ re ho and central crack in plat s of finite and infinite extension. Th values of the NSIFs d riv d according to Gross a Mend ls n have b en compared with th se ob aine by means of the approximat methods, by using coarse FE meshes. © 2016 The Authors. Publishe by Elsevi r B.V. Peer-review under esponsibility of the Scientific Committee of ECF21. Keywords: NSIFs; Strain energy density; control radius; mixed mode; FE analysis. 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.

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

* Corresponding author. Tel.: +39 0444 998747. E-mail address: berto@gest.unipd.it * Corresponding author. Tel.: +39 0444 998747. E-mail ad ress: berto@gest.unipd.it

* 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 r sponsibility 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.2016.06.230