PSI - Issue 5

ScienceDirect Available online at www.sciencedirect.com Av ilable o line at ww.sciencedire t.com Sci ceDirect Structural Integrity Procedia 00 (2016) 000 – 000 Procedia Structu al Integrity 5 (2017) 584–591 Available online at www.sciencedirect.com ScienceDirect 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. 2nd International Conference on Structural Integrity, ICSI 2017, 4-7 September 2017, Funchal, Madeira, Portugal An Optimized RBF Analysis of an Isotropic Mindlin Plate in Bending Behzad V. Farahani a,b, *, Jose Berardo b , Jorge Belinha b , A. J. M. Ferreira b , Paulo J. Tavares a , Pedro Mor ira a a INEGI, Institute of Science and Innovation in Mechanical and Industrial Engineering, Dr. Roberto Frias Street, 400, 4200-465, Porto, Portugal. b FEUP, Faculty of Engineering, University of Porto, Dr. Roberto Frias Street, 4200-465, Porto, Portugal. This study focuses on the numerical analysis of an isotropic plate under a uniform distributed load. The problem is solved considering the Reissner-Mindlin plate deformation theory combined with a Radial Basis Function (RBF) meshless method. Thus, in this work, the RBF meshless method formulation for the analysis of thick isotropic plates assuming a first order shear deformation theory is shown with detail. Additionally, the essential boundary conditions, material properties and geometrical characteristics of the model are fully presented. In this work, the nonzero laminate stiffnesses are determined through equations of motion in terms of displacements for homogeneous laminates. The transverse displacement results are evaluated for various thickness values where the plate is simply supported in all edges. Additionally, the shape parameter governing the RBF formulation is optimized using several mesh densities. The obtained numerical results are compared to the exact analytical solution available in the literature. Accurate RBF solutions are obtained, supporting the efficiency of the numerical methodology. © 2017 The Authors. Published by Elsevier B.V. Peer-review under responsibil ty of the Scientific Committee of ICSI 2017. Keywords: Radial Basis Function; Mindlin Plate; Single-Layered Laminate; Bending Stiffness; Transverse displacement; Shape Parameter. 2nd International Conference on Structural Integrity, ICSI 2017, 4-7 September 2017, Funchal, Madeira, Portugal An Optimized RBF Analysis of an Isotropic Mindlin Plate in Bending Behzad V. Farahani a,b, *, Jose Berardo b , Jorge Belinha b , A. J. M. Ferreira b , Paulo J. Tavares a , Pedro Moreira a a INEGI, Institute of Science and Innovation in Mechanical and Ind strial Engineering, Dr. Roberto Frias Street, 400, 4200-465, Porto, Portugal. b FEUP, Faculty of Engineering, University of Porto, Dr. Roberto Frias Street, 4200-465, Porto, Portugal. Abstract This study focu es on the numerical analys s of an isotropic plate under a uniform distributed load. The problem is solved cons dering t eissner-Mindlin plate deformation theory comb ned w th a Radial Basis Functio (RBF) meshless meth d. Thus, in this work, the RBF mesh ess method formulatio for the a alysis f th ck isotropic plates assumi g a first o der she deformati n ory is shown with detail. Addi ionally, the sse tial boundary conditions, material properties and geometrical character stics of the model ar fully presented. In this work, the nonzero laminate stiffnesses are determined through equations of motion in terms of displacements for homogeneous laminates. The transverse dis lacement results a e evaluated for va io s thickness values where the plate is simply supported in all edg s. Additionally, the shape parame er governing the RBF formul tion is optimized using several mesh densi es. Th o taine n merical results are compared to the exact analytical solution available in the literature. Accurate RBF solutions are obtained, supporting the fficiency of the numerical methodology. © 2017 The Au ho s. Publ shed by Elsevier B.V. Peer-review under responsibility of the Scie tific Committe o ICSI 2017. Keywords: Radial Basis Function; Mindlin Plate; Single-Layered Laminate; Bending Stiffness; Transverse displacement; Shape Parameter. © 2017 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of ICSI 2017 © 2016 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of PCF 2016. Abstract

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

2452-3216 © 2016 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of PCF 2016. 2452-3216  2017 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of ICSI 2017 10.1016/j.prostr.2017.07.018 * Corresponding author. Tel.: +351 218419991. E-mail address: amd@tecnico.ulisboa.pt 2452 3216 © 2017 Th Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of ICSI 2017. 2452-3216 © 2017 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of ICSI 2017. * Correspon ing author. Tel.: +0-000-000-0000 ; fax: +0-000-000-0000 . E-mail address: Behzad.farahani@fe.up.pt * Corresponding author. Tel.: +0-000-000-0000 ; fax: +0-000-000-0000 . E-mail address: Behzad.farahani@fe.up.pt