PSI - Issue 12

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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. AIAS 2018 International Conference on Stress Analysis FEM-DBEM approach to simulate crack propagation in a turbine vane segment undergoing a fatigue load spectrum Venanzio Giannella a , Edoardo Vivo b , Massimo Mazzeo b , Roberto Citarella a * a Dept. of Industrial Engineering, U iversity of Salerno, via Giovanni Paolo II, Fisciano (SA), Italy b GE- Avio, Viale Giuseppe Luraghi, 20, Pomigliano d’Arco (NA), Italy In this work a thermo-mechanical fatigue application, related to a crack propagation in an aircraft turbine vane undergoing a complex load spectrum, is simulated. A computationally efficient FEM-DBEM submodelling approach, whose implementation leverages on the principle of linear superposition, is adopted. When tackling a crack propagation problem with a FEM-DBEM combined approach, the global analysis is generally worked out by FEM whereas the fracture problem is solved in a DBEM environment. In particular, a DBEM submodel is extracted from the global uncracked FEM model and, generally, is loaded on the boundaries with temperatures and either displacements or tractions; then the crack propagation is simulated by repeated thermal-stress DBEM analyses. Differently from that, the proposed equivalent approach solves the crack propagation problem by adopting a simpler pure stress DBEM analyses in which the boundary conditions, in terms of tractions, are just needed on the DBEM crack faces. Such tractions are evaluated by the FEM global analysis along a virtual surface traced by the advancing crack (the FEM model is uncracked). Such an approach provides accuracy enhancement and computational advantages. © 2018 The Authors. Published by Elsevier B.V. This is an open access article under the CC BY-NC-ND icense (http://creativecommons.org/licenses/by-nc-nd/3.0/) Peer-review under responsibility of the Scientific Committee of AIAS 2018 International Conference on Stress Analysis. © 2018 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/3.0/) Peer-review under responsibility of the Scientific Committee of AIAS 2018 International Conference on Stress Analysis. AIAS 2018 International Conference on Stress Analysis FEM-DBEM approach to simulate crack propagation in a turbine vane s gment undergoing a fatigu load spectrum Venanzio Giannella a , Edoardo Vivo b , Massimo Mazzeo b , Roberto Citarella a * a Dept. of Industrial Engineering, University of Salerno, via Giovanni Paolo II, Fisciano (SA), Italy b GE- Avio, Viale Giuseppe Luraghi, 20, Pomigliano d’Arco (NA), Italy Abstract In this work a thermo-mechanical fatigue application, related to a crack propagation in an aircraft turbine vane undergoing a complex load spe trum, is simulated. A computationally efficient FEM-DBEM submodelling approach, whose implementation leverages on the principle of linear superposition, is adopted. When tackling a crack propagation problem with a FEM-DBEM combined approach, the global analysis is generally worked out by FEM whereas the fracture problem is solved in a DBEM environment. In particular, a DBEM submodel is extracted from the global uncracked FEM model and, generally, is loaded on the boundaries with temperatures and either displacements or tractions; then the crack propagation is simulated by repeated thermal-stress DBEM analyses. Differently fro that, the proposed equivalent approach solves the crack propagation problem by adopting a simpler pur stress DBEM analyses in which the boundary conditions, in terms of tractions, are just needed on the DBEM crack faces. Such tractions are evaluated by the FEM global analysis along a virtual surfac traced by the advanc ng crack (the FEM model is uncracked). Such an approach p ovides accuracy enhancement and computational advantages. © 2018 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/3.0/) Peer-review under responsibility of the Scientific Committee of AIAS 2018 International Conference on Stress Analysis. Abstract

© 2016 The Authors. Published by Elsevier B.V. Peer-review under responsibility of the Scientific Committee of PCF 2016. Keywo ds: FEM-DBEM; fatigue crack-growth; turbine vane; load sp ctrum. Keywords: FEM-DBEM; fatigue crack-growth; turbine vane; load spectrum.

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

* Corresponding author. Tel.: +39-089-96-4111; fax: +39-089-96-4111. E-mail address: rcitarella@unisa.it * Corresponding author. Tel.: +39-089-96-4111; fax: +39-089-96-4111. E-mail address: rcitarella@unisa.it

2452-3216 © 2018 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/3.0/) Peer-revi w u er responsibility of the Scientific Committee of AIAS 2018 International Conference on Stress Analysis. 2452-3216 © 2018 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/3.0/) Peer-review under responsibility of the Scientific ommittee of AIAS 2018 International Conference on Stress Analysis.

* 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  2018 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/3.0/) Peer-review under responsibility of the Scientific Committee of AIAS 2018 International Conference on Stress Analysis. 10.1016/j.prostr.2018.11.070