PSI - Issue 11

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ScienceDirect Available online at www.sciencedirect.com Av ilable o line at www.sciencedirect.com Sci ceDirect Structural Integrity Procedia 00 (2016) 000 – 000 Procedia Structu al Integrity 11 (2018) 428–435 Structural Integ rity Procedia 00 ( 2018) 000–000 Structural Integ rity Procedia 00 ( 2018) 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. ract European he m. 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Although th these materia YS code 3D e ard tests were vior to uniaxial edrical 8 and 2 ional FE mode ls have been u over, fracture nding failure b avior according orced masonry right © 2018 E review under r ords: masonry; c ritage and mod ese structures ls as structura lements in the made and calib a diagonal 0 odes tridim ls which use e sed to study th energies based etween these tw to experimenta specimens. lsevier B.V. A esponsibility o omposites; TRM ern buildings have a low cap l system in ma num rical o rated using res ompression in ensional eleme leme t solid65 e compression- cohesive z o materials. Th l results and w ll rights reserve f the CINPAR ; mechanical pro have a very h acity to r sist t ny seismic ar delling of mas ults of experim brick sam les. nts to represen as finite elem tension failure es have been a ese modelling will be used as a d. 2018 organizer perties; FEM . Gonzalez ado 99, 03080, A igh seismic vu ension or shea eas. The main onry structure e tal tests. In p The umerical t brick and mo ent to represen surface, addi dded to contac g methods prove base to devel s lnerability due r stresses, even obj ctive of t s. For this pur articular, this l micromodel h rtar, such as so t masonry beh g a linear harde ts between m to be a valid t op future param to their maso n wadays som his p per is th pose, FE mode d cument will s been develop lid185 and sol avior. Drucker ning-softening ortar and brick echnique to sim etric FEM ana nry-based stru me new building he use of high ls correspondi analyze the res oped using non id186, in contr Prager and Ra -dilatatio beh ks, in order to ulate brick ma lysis to study ctural s are order ng to istant linear ast to nkine avior. ll w sonry TRM Abst Many syste using ANS stand beha hexa tradit mode More debo beha reinf Copy Peer Keyw

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

2452 Peer-r 2452 Peer-r * C E * C E 3216 Copyright evi w u er resp 3216 Copyright eview under resp Corresponding aut -mail address: si orresponding aut E-mail ad ress: si

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B.V. All rights re CINPAR 2018 o B.V. All rights re CINP R 2018 o

served. rganizers. served. rganizers.

* Corresponding author. Tel.: +351 218419991. E-mail address: amd@tecnico.ulisboa.pt

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