PSI - Issue 7

ScienceDirect Available online at www.sciencedirect.com

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 7 (2017) 438–445 Structural Integrity Procedia 00 (2017) 000–000 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. Copyright © 2017 The Authors. ublishe by Elsevier B.V. Peer-review und responsibility of the Scientific Co mittee of the 3rd International Symposium on Fatigue Design and Material Defects. Marton Groza a* , Yves Nadot b , Karoly Varadi a a TU Budapest, Department of Machine and Product Design, M ű egyetem rkp. 3, Budapest 1111, Hungary b Institut Pprime, CNRS, ISAE-ENSMA, Université de Poitiers, Téléport 2, 1 Avenue Clément Ader, 86961 Futuroscope Chasseneuil Cedex, France Abstract With the analysis example of a cast iron component a Finite Element Analysis (FEA) based modelling and post-processing methodology is proposed for the multiaxial high-cycle fatigue assessment of surface defects. Methods are proposed for the measurement and mechanical description of surface defects using an ellipsoid simplification and the well-known size parameter fromMurakami (2002). Different methods are compared for the stress-computation near surface defects: elastic FEA, elastic-plastic FEA with nonlinear kinematic hardening material model, and analytical calculations with the Equivalent Inclusion Method from Eshelby (1957). The Defect Stress Gradient (DSG) approach from Vincent et al. (2014) is applied to predict crack initiation, whereby a new method is proposed for the estimation of the stress gradient, which allows the presentation of the DSG utilisation factor results field. © 2017 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of the 3rd International Symposium on Fatigue Design and Material Defects. Keywords: multiaxial fatigue; crack initiation; FEA; stress gradient; surface defects; nodular cast iron 1. Introduction Fatigue behaviour of defective c st iron Marton Groza a* , Yves Nadot b , Karoly Varadi a a TU Budapest, Department of Machine and Product Design, M ű egyetem rkp. 3, Budapest 1111, Hungary b Institut Pprime, CNRS, ISAE-ENSMA, Université de Poitiers, Téléport 2, 1 Avenue Clément Ader, 86961 Futuroscope Chasseneuil Cedex, France Abstract With the a alysis example of a ast iron component a Finite Elem nt Analysis (FEA) based modelling and post-processing methodology is proposed o the multiaxial high-cycle fatigue assess ent of surf ce defects. Method are proposed for the measurement and mechanical description of surface defects usi g an ellipsoid simplification and the well-known size parameter fromMurakami (2002). Different metho s are compared for the stress-computation near surface defects: elastic FEA, elastic-plastic FE with nonlinear kinematic har ening material model, and analytical calculations with t Equivalent Inclusion Method from Eshelby (1957). The Defect Stress Gradient (DSG) approach from Vincent et al. (2014) is applied to predict crack initiation, whereby a n w method is proposed fo the estimation of the stress gradient, which allows the pres nt tion of the DSG utilisation factor results field. © 2017 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of the 3rd International Symposium on Fatigue Design and Material D fects. Keywords: multiaxial fatigue; crack initiation; FEA; stress gradient; surface defects; nodular cast iron © 2016 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of PCF 2016. Surface def cts play a major role in the cast material fatigue, since they are the most likely cause of crack initiation leading to fractur in the high cycle fatigue regime. Th fatigue design of industrial cast components is therefore 1. Introduction Surface defects play a major role in the cast material fatigue, since they are the most likely cause of crack initiation leading to fractur in the high cycle fatigue regime. The fatigue design of industrial cast components is therefore Keywords: High Pressure Turbine Blade; Creep; Finite Element Method; 3D Model; Simulation. 3rd International Symposium on Fatigue Design and Material Defects, FDMD 2017, 19-22 September 2017, Lecco, Italy 3rd International Symposium on Fatigue Design and Material Defects, FDMD 2017, 19-22 September 2017, Lecco, Italy Fatigue behaviour of defective cast iron

* Corresponding author. Tel.: +36-1-463-1349. E-mail address: groza.marton@gt3.bme.hu * Corresponding author. Tel.: +36-1-463-1349. E-mail address: groza.marton@gt3.bme.hu

2452-3216 © 2017 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of the 3rd International Symposium on Fatigue Design and Material Defects. 2452-3216 © 2017 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of the 3rd International Symposium on Fatigue Design and Material Defects.

* 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.

2452-3216 Copyright  2017 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of the 3rd International Symposium on Fatigue Design and Material Defects. 10.1016/j.prostr.2017.11.110