PSI - Issue 1

ScienceDirect Procedia Structural Integrity 1 (2016) 234–241 Available online at www.sciencedirect.com Av ilable o line at ww.sciencedire t.com ScienceDirect Structural Integ ity Procedia 00 (2016) 000 – 000 Available online at www.sciencedirect.com ScienceDirect StructuralIntegrity Procedia 00 (2016) 000 – 000 il l li i i t t l t it i

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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. XV Portuguese Conference on Fracture, PCF 2016, 10-12 February 2016, Paço de Arcos, Portugal Buckling of cracked plate reinforced Salem Cherif Sadek a , Tamine tawfik a a LCGE, Faculté de Genie Maritime, Université des Sciences et de Technologie d’Oran Mohamed Boudiaf, 31000,Algeria Abstract The objective of this paper is to numerically analyze the buckli g of reinforced structures (stiffened plate) cracked under compressive stress by considering the evolution of cracks and its orientation. Numerical modeling and calculation by the finite element method, estimated the critical load for compression panel. The work presented in the article was inspired by sever l publications that related to this field. Brighent (2005) ha e studied the behavior of elastic buckling of rectangular cracked thin plate for different boundaries conditions. Following these calculations, a calibration function was derived to estimate the load ratio ψ to the compression function of the crack length and its inclination. We found that the variation of the critical stress is proportional to the crack dimensions. In buckling, a transverse crack is more stable than a longitudinal crack. © 2016 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of PCF 2016. Keywords: Buckling; Plate; Crack; Stiffness; 1. In rod ction The stability of the plate increases with the increase of the thickness of the plate. An efficient solution is obtained by keeping the thickness of the plate as small as possible by introducing reinforcements. TIMOSHENKO and GERE (1961) clearly explained and applied the bar theory in linear buckling problems in several concrete cases. R. Brighenti (2005) has studied the behavior elastic buckling of rectangular thin plates in different cracks for different boundary conditions. Numerical results proved that the effects of cracks under the compression buckling phenomenon dependent on boundary conditions of the plate. K. Ghavami and M.R. Khedmati (2006) worked on stiffened plates Submitted to axial compression load to failure. a , lt i iti , i it i t l i i , , l i calculation by the finite element method, estimated the critical load for compression panel. The h a v A . y E . . Peer-review under responsibility of the Scientific C mmittee of . li ; l t ; ; ti ; u explained and applied the bar theory in linear buckling problems in several concrete cases. R. Brighen or elastic b kling Copyright © 2015 The Au hors. Published by Elsevi r B.V. This is an open access articl un er the CC BY-NC-ND license (http://creativecommons.org/licenses/by-nc-nd/4.0/ . Peer-review under resp nsibil ty of the Scientific Committee of PCF 2016. © 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.: +0-000-000-0000 ; fax: +0-000-000-0000 . E-mail address: sadek103@gmail.com i t . l.: ; : .

* 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 PCF 2016. l i . . . t . li

2452-3216 © 2016 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of PCF 2016. Copyright © 2015 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 PCF 2016. 10.1016/j.prostr.2016.02.032