PSI - Issue 5

ScienceDirect Available online at www.sciencedirect.com Av ilable o line at ww.sciencedire t.com ienceDirect Structural Integrity Procedia 00 (2016) 000 – 000 Procedia Structu al Integrity 5 (2017) 239–246 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

www.elsevier.com/locate/procedia 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. Analysis of fatigue crack propagation in laser sintering metal L.F.P. Borrego a,b *, F.V. Antunes a , J.A.M. Ferreira a , J.D. Costa a , C. Capela a,c a CEMMPRE, University of Coimbra, Department of Mechanical Engineering, Rua Luís Reis Santos, 3030-788, Coimbra, Portugal b Instituto Politécnico de Coimbra, ISEC, Department of Mechanical Engineering,Rua Pedro Nunes, 3030-199 Coimbra, Portugal c Instituto Politécnico de Leiria, Department of Mechanical Engineering, ESTGMorro do Lena – Alto Vieiro, 2400-901 Leiria, Portugal. Abstract Laser sintering metal has recently been used in the manufacture of components for different applications like aerospace or medicine. The approach to engineering design based on the cracks propagation assumption applying the conc pts of line elastic fracture mechanics (LEFM) is c mmonly used for aerospace engineering. However, fatigue crack propagation is linked to irreversible and non-linear mechanisms at the crack tip, therefore LEFM parameters can be successfully replaced by non-linear crack parameters, namely the plastic CTOD. A model linking da/dN with plastic CTOD is proposed here to characterize fatigue crack propagation. A comparison is made with other materials showing that for the same plastic CTOD the laser sintering material has a relatively large crack growth rate. © 2017 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of ICSI 2017. Keywords: Laser sintering material; fatigue crack propagatio ; plastic CTOD 1. Introduction Laser sintering metal (LSM) has recently been used in the manufacture of components for different applications like aerospace or medicine. Many studies, mainly focused on the influence of sintering parameters and selection of metal powder on microstructure of the sintered parts, state that for some materials, LSM parts are able to offer static mechanical properties comparable to the properties of conventionally bulk materials. However, on service the 2nd International Conference on Structural Integrity, ICSI 2017, 4-7 September 2017, Funchal, Madeira, Portugal Analysis of fatigue crack propagation in laser sintering metal L.F.P. Borrego a,b *, F.V. Antunes a , J.A.M. Ferreira a , J.D. Costa a , C. Capela a,c a CEMMPRE, University of Coimbra, Department of Mechanic l Engineering, Rua Luís Reis Santo 788, Coi bra, Portugal b Ins itut Polité nico d Coimbra, ISEC, Departme t of Mechanical Engineering,Rua P dro Nunes, 3030-199 Coimbra, Portugal c Instituto Politécnico de Leiria, Department of Mechanical Engineering, ESTGMorro do Lena – Alto Vieiro, 2400-901 Leiria, Portugal. Abstract Laser sintering metal has recently b en us d in the manufacture of components for different applications lik aerospace or m dicine. The approach to en ineering design based on th cr cks propagatio assumpti n applying th once ts of linear elastic fracture m chanics (LEFM) is co monly used for aerospace engineering. However, fatigue rack propagation is linked to irreversible and non-linear mechanisms at the rack tip, therefore LEFM p rameters can be successfully replaced by non-linear crack parameters, namely the plastic CTOD. A o el linking da/dN with plastic CTOD is proposed here to characterize fatigue crack propagation. A comparison is made with other materials showing that for the same plastic CTOD the laser sintering material has a relatively large crack growth rate. © 2017 The Authors. Publ shed by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of ICSI 2017. Keywords: Laser sintering material; fatigue crack propagation; plastic CTOD 1. Introduction L ser sintering etal (LS ) has rec ntly been used in the manufacture of compo ents for differe t applications like aerospace or medicine. Many studies, mainly focused on the influ nce of sintering paramet rs and selection of tal powder n microstructure of the sintered parts, state that for some materials, LSM parts are able to offer static mechanical properties comparable to the properties of conventionally bulk materials. However, on service the © 2017 The Authors. Published by Elsevier B.V. Peer-review under r sponsibility 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. Keywords: High Pressure Turbine Blade; Creep; Finite Element Method; 3D Model; Simulation. 2nd International Conference on Structural Integrity, ICSI 2017, 4-7 September 2017, Funchal, Madeira, Portugal

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.2017.07.123 * 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. * Corresponding author. Tel.: +351 962560101; fax: +351 239790331. E-mail address: borrego@isec.pt * Corresponding author. Tel.: +351 962560101; fax: +351 239790331. E-mail address: borrego@isec.pt